NACA 64(1)-212 MOD A (n64212ma-il)
NACA 64(1)-212 MOD A - NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil
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(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 Source dat file The dat file is in Lednicer format |
NACA 64(1)-212 MOD A
30. 28.
0.0000000 0.0000000
0.0017515 0.0139677
0.0048357 0.0209074
0.0088714 0.0263278
0.0138847 0.0315286
0.0188679 0.0352297
0.0288103 0.0414320
0.0387467 0.0473345
0.0486491 0.0515373
0.0617421 0.0581767
0.0917591 0.0646775
0.1164151 0.0696854
0.1656920 0.0755010
0.2149875 0.0788158
0.2642925 0.0811300
0.3135933 0.0827444
0.3628836 0.0828386
0.4121608 0.0822930
0.4614075 0.0797175
0.5105944 0.0756329
0.5597372 0.0703291
0.6088307 0.0640261
0.6578783 0.0568937
0.7068729 0.0490923
0.7558185 0.0407918
0.8047181 0.0321620
0.8535675 0.0234733
0.9023817 0.0149853
0.9511766 0.0070179
1.0000000 0.0000000
0.0000000 0.0000000
0.0013356 -.0068281
0.0041940 -.0111861
0.0080518 -.0146640
0.0129090 -.0172616
0.0226835 -.0194576
0.0324820 -.0204537
0.0570021 -.0217444
0.0962359 -.0237295
0.1354696 -.0257145
0.1747054 -.0275996
0.2139372 -.0296847
0.2531670 -.0318697
0.3127909 -.0349728
0.3616514 -.0367204
0.4105350 -.0373181
0.4594425 -.0362260
0.5084032 -.0339448
0.5574017 -.0307641
0.6064432 -.0269042
0.6555237 -.0225549
0.7046501 -.0178766
0.7538183 -.0130790
0.8030236 -.0083921
0.8522694 -.0041262
0.9015374 -.0007209
0.9508063 0.0012641
1.0000000 0.0000000
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Polars for NACA 64(1)-212 MOD A (n64212ma-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64212ma-il | 50,000 | 9 | 29.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 50,000 | 5 | 28.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 100,000 | 9 | 42.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 100,000 | 5 | 38.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 200,000 | 9 | 49.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 200,000 | 5 | 48.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 500,000 | 9 | 68.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 500,000 | 5 | 68.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 1,000,000 | 9 | 83.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 1,000,000 | 5 | 79.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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