Naca 6 Series
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(n63010a-il) NACA 63A010 AIRFOIL NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63012a-il) NACA 63012A AIRFOIL NACA 63-012A airfoil Max thickness 12% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63015a-il) NACA 63-015A AIRFOIL NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63210-il) NACA 63-210 AIRFOIL NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Source UIUC Airfoil Coordinates Database
(n63212-il) NACA 63-212 AIRFOIL NACA 63(1)-212 airfoil Max thickness 12% at 34.9% chord Max camber 1.1% at 55% chord Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to
NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n63215b-il) NACA 63(2)-215 MOD B NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n63415-il) NACA 63-415 AIRFOIL NACA 63(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012-il) NASA/LANGLEY 64-012 AIRFOIL NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL
comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter
NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015-il) NACA 642-015 AIRFOIL NACA 64(2)-015 airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n64110-il) NACA 64-110 AIRFOIL NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212
Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to
NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212ma-il) NACA 64(1)-212 MOD A NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Source UIUC Airfoil Coordinates Database
(n64215-il) NACA 64-215 AIRFOIL NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL
comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison NACA 66(4)-021 airfoil Lednicer format Max thickness 21% at 45% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206 NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Coordinates Database
(naca63209-il) NACA 63-209 NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
(naca632615-il) NACA 63(2)-615
Airfoil details Send to airfoil plotter NACA 63(2)-615 airfoil Add to comparison Max thickness 15% at 34.8% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca632a015-il) NACA 63(2)A-015
Airfoil details Send to airfoil plotter NACA 63(2)A-015 airfoil Add to comparison Max thickness 15% at 37.1% Lednicer format chord dat file Max camber 1.7% at 14.6% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca633018-il) NACA 63(3)-018
(naca633218-il) NACA 63(3)-218
(naca633418-il) NACA 63
Airfoil details Send to airfoil plotter Add to comparison NACA 63(3)-018 airfoil Lednicer format Max thickness 18% at 33.9% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(3)-218 airfoil Add to comparison Max thickness 18% at 34.9% Lednicer format chord dat file Max camber 1.1% at 24.9% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca633618-il) NACA 63(3)-618
(naca634221-il) NACA 63(4)-221
(naca634421-il) NACA 63(4)-421
(naca63a210-il) NACA 63A210
(naca641112-il) NACA 64(1)-112
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 63(3)-618 airfoil Add to comparison Max thickness 18% at 34.7% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(4)-221 airfoil Add to comparison Max thickness 21% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(4)-421 airfoil Add to comparison Max thickness 21% at 34.8% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63A210 airfoil Add to comparison Max thickness 10% at 34.9% Lednicer format chord dat file Max camber 1.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206 NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64208-il) NACA 64-208 NACA 64-208 airfoil Max thickness 8% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64209-il) NACA 64-209 NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210 NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca642215-il) NACA 64(2)-215
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64(2)-215 airfoil Add to comparison Max thickness 15% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca642415-il) NACA 64(2)-415
(naca643218-il) NACA 64(3)-218
Airfoil details Send to airfoil plotter NACA 64(2)-415 airfoil Add to comparison Max thickness 15% at 34.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 64(3)-218 airfoil Add to comparison Max thickness 18% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca643418-il) NACA 64(3)-418 NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618 NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221
(naca644421-il) NACA 64(4)-421
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64(4)-221 airfoil Add to comparison Max thickness 21% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%
Airfoil details Send to airfoil plotter Add to comparison NACA 64A010 airfoil Lednicer format Max thickness 10% at 40% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca64a210-il) NACA 64A210 NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a410-il) NACA 64A410
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64A410 airfoil Add to comparison Max thickness 10% at 39.9% Lednicer format chord dat file Max camber 2.7% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca651212-il) NACA 65(1)-212 NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca651212a06-il) NACA 65(1)-212 a=0.6
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 65(1)-212 a=0.6 airfoil Add to comparison Max thickness 12% at 40% Lednicer format chord dat file Max camber 1.5% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca651412-il) NACA 65(1)-412
Airfoil details Send to airfoil plotter NACA 65(1)-412 airfoil Add to comparison Max thickness 12% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206 NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209 NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65210-il) NACA 65-210 NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652215-il) NACA 65(2)-215 NACA 65(2)-215 airfoil Max thickness 15% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652415-il) NACA 65(2)-415
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison
NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652415a05-il) NACA 65(2)-415 a=0.5
(naca653218-il) NACA 65(3)-218
(naca653618-il) NACA 65(3)-618
(naca65410-il) NACA 65-410
(naca654221-il) NACA 65(4)-221
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison NACA 65(2)-415 a=0.5 airfoil Lednicer format Max thickness 15% at 39.9% dat file chord Selig format dat file Max camber 3% at 45% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65(3)-218 airfoil Add to comparison Max thickness 18% at 39.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65(3)-618 airfoil Add to comparison Max thickness 18% at 39.8% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65-410 airfoil Add to comparison Max thickness 10% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca654421-il) NACA 65(4)-421
(naca654421a05-il) NACA 65(4)-421 a=0.5
(naca66-018-il) NACA 66-018
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 65(4)-421 airfoil Add to comparison Max thickness 21% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison NACA 65(4)-421 a=0.5 airfoil Lednicer format Max thickness 21% at 39.9% dat file chord Selig format dat file Max camber 3% at 45% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison NACA 66-018 airfoil Lednicer format Max thickness 18% at 45% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca661212-il) NACA 66(1)-212 NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66206-il) NACA 66-206 NACA 66-206 airfoil Max thickness 6% at 45% chord Max camber 1.1% at 50%
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
chord Source UIUC Airfoil Coordinates Database
(naca66209-il) NACA 66-209 NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210 NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca662215-il) NACA 66(2)-215 NACA 66(2)-215 airfoil Max thickness 15% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca662415-il) NACA 66(2)-415 NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca663218-il) NACA 66(3)-218 NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca663418-il) NACA 66(3)-418
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison
NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca664221-il) NACA 66(4)-221 NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca671215-il) NACA 67 NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
(n63012a-il) NACA 63012A AIRFOIL NACA 63-012A airfoil Max thickness 12% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63015a-il) NACA 63-015A AIRFOIL NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63210-il) NACA 63-210 AIRFOIL NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Source UIUC Airfoil Coordinates Database
(n63212-il) NACA 63-212 AIRFOIL NACA 63(1)-212 airfoil Max thickness 12% at 34.9% chord Max camber 1.1% at 55% chord Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to
NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n63215b-il) NACA 63(2)-215 MOD B NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n63415-il) NACA 63-415 AIRFOIL NACA 63(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012-il) NASA/LANGLEY 64-012 AIRFOIL NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL
comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter
NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015-il) NACA 642-015 AIRFOIL NACA 64(2)-015 airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n64110-il) NACA 64-110 AIRFOIL NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212
Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to
NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212ma-il) NACA 64(1)-212 MOD A NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Source UIUC Airfoil Coordinates Database
(n64215-il) NACA 64-215 AIRFOIL NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL
comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison NACA 66(4)-021 airfoil Lednicer format Max thickness 21% at 45% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206 NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Coordinates Database
(naca63209-il) NACA 63-209 NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
(naca632615-il) NACA 63(2)-615
Airfoil details Send to airfoil plotter NACA 63(2)-615 airfoil Add to comparison Max thickness 15% at 34.8% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca632a015-il) NACA 63(2)A-015
Airfoil details Send to airfoil plotter NACA 63(2)A-015 airfoil Add to comparison Max thickness 15% at 37.1% Lednicer format chord dat file Max camber 1.7% at 14.6% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca633018-il) NACA 63(3)-018
(naca633218-il) NACA 63(3)-218
(naca633418-il) NACA 63
Airfoil details Send to airfoil plotter Add to comparison NACA 63(3)-018 airfoil Lednicer format Max thickness 18% at 33.9% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(3)-218 airfoil Add to comparison Max thickness 18% at 34.9% Lednicer format chord dat file Max camber 1.1% at 24.9% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca633618-il) NACA 63(3)-618
(naca634221-il) NACA 63(4)-221
(naca634421-il) NACA 63(4)-421
(naca63a210-il) NACA 63A210
(naca641112-il) NACA 64(1)-112
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 63(3)-618 airfoil Add to comparison Max thickness 18% at 34.7% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(4)-221 airfoil Add to comparison Max thickness 21% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63(4)-421 airfoil Add to comparison Max thickness 21% at 34.8% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 63A210 airfoil Add to comparison Max thickness 10% at 34.9% Lednicer format chord dat file Max camber 1.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206 NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64208-il) NACA 64-208 NACA 64-208 airfoil Max thickness 8% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64209-il) NACA 64-209 NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210 NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca642215-il) NACA 64(2)-215
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64(2)-215 airfoil Add to comparison Max thickness 15% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca642415-il) NACA 64(2)-415
(naca643218-il) NACA 64(3)-218
Airfoil details Send to airfoil plotter NACA 64(2)-415 airfoil Add to comparison Max thickness 15% at 34.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 64(3)-218 airfoil Add to comparison Max thickness 18% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca643418-il) NACA 64(3)-418 NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618 NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221
(naca644421-il) NACA 64(4)-421
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64(4)-221 airfoil Add to comparison Max thickness 21% at 34.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%
Airfoil details Send to airfoil plotter Add to comparison NACA 64A010 airfoil Lednicer format Max thickness 10% at 40% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca64a210-il) NACA 64A210 NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a410-il) NACA 64A410
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 64A410 airfoil Add to comparison Max thickness 10% at 39.9% Lednicer format chord dat file Max camber 2.7% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca651212-il) NACA 65(1)-212 NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca651212a06-il) NACA 65(1)-212 a=0.6
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 65(1)-212 a=0.6 airfoil Add to comparison Max thickness 12% at 40% Lednicer format chord dat file Max camber 1.5% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca651412-il) NACA 65(1)-412
Airfoil details Send to airfoil plotter NACA 65(1)-412 airfoil Add to comparison Max thickness 12% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206 NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209 NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65210-il) NACA 65-210 NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652215-il) NACA 65(2)-215 NACA 65(2)-215 airfoil Max thickness 15% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652415-il) NACA 65(2)-415
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison
NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca652415a05-il) NACA 65(2)-415 a=0.5
(naca653218-il) NACA 65(3)-218
(naca653618-il) NACA 65(3)-618
(naca65410-il) NACA 65-410
(naca654221-il) NACA 65(4)-221
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison NACA 65(2)-415 a=0.5 airfoil Lednicer format Max thickness 15% at 39.9% dat file chord Selig format dat file Max camber 3% at 45% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65(3)-218 airfoil Add to comparison Max thickness 18% at 39.9% Lednicer format chord dat file Max camber 1.1% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65(3)-618 airfoil Add to comparison Max thickness 18% at 39.8% Lednicer format chord dat file Max camber 3.3% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter NACA 65-410 airfoil Add to comparison Max thickness 10% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database Airfoil details Send to airfoil plotter Add to comparison
NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca654421-il) NACA 65(4)-421
(naca654421a05-il) NACA 65(4)-421 a=0.5
(naca66-018-il) NACA 66-018
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter NACA 65(4)-421 airfoil Add to comparison Max thickness 21% at 39.9% Lednicer format chord dat file Max camber 2.2% at 50% Selig format dat file chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison NACA 65(4)-421 a=0.5 airfoil Lednicer format Max thickness 21% at 39.9% dat file chord Selig format dat file Max camber 3% at 45% chord Source dat file Source UIUC Airfoil Coordinates Database
Airfoil details Send to airfoil plotter Add to comparison NACA 66-018 airfoil Lednicer format Max thickness 18% at 45% dat file chord Selig format dat file Max camber 0% at 0% chord Source dat file Source UIUC Airfoil Coordinates Database
(naca661212-il) NACA 66(1)-212 NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66206-il) NACA 66-206 NACA 66-206 airfoil Max thickness 6% at 45% chord Max camber 1.1% at 50%
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
chord Source UIUC Airfoil Coordinates Database
(naca66209-il) NACA 66-209 NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210 NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca662215-il) NACA 66(2)-215 NACA 66(2)-215 airfoil Max thickness 15% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca662415-il) NACA 66(2)-415 NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca663218-il) NACA 66(3)-218 NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca663418-il) NACA 66(3)-418
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison
NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca664221-il) NACA 66(4)-221 NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca671215-il) NACA 67 NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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