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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.45 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212ma-il-1000000.txt
Download as CSV file: xf-n64212ma-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4156   0.09816   0.09642  -0.0292   1.0000   0.0205
 -10.250  -0.4207   0.09214   0.09041  -0.0327   1.0000   0.0206
 -10.000  -0.4304   0.08564   0.08392  -0.0361   1.0000   0.0207
  -9.750  -0.4263   0.08321   0.08152  -0.0366   1.0000   0.0209
  -9.500  -0.4249   0.07975   0.07808  -0.0383   1.0000   0.0210
  -9.250  -0.4237   0.07637   0.07472  -0.0402   1.0000   0.0211
  -8.750  -0.4057   0.06341   0.06165  -0.0608   0.9510   0.0215
  -8.500  -0.4147   0.05955   0.05757  -0.0630   0.9058   0.0217
  -8.250  -0.4196   0.05676   0.05462  -0.0624   0.8807   0.0220
  -8.000  -0.4196   0.05400   0.05173  -0.0619   0.8630   0.0227
  -7.750  -0.4501   0.04285   0.03998  -0.0605   0.8496   0.0243
  -7.500  -0.4372   0.04114   0.03816  -0.0598   0.8366   0.0244
  -7.250  -0.4223   0.03945   0.03637  -0.0593   0.8250   0.0246
  -7.000  -0.4058   0.03806   0.03486  -0.0587   0.8109   0.0248
  -6.750  -0.3883   0.03645   0.03313  -0.0581   0.7960   0.0250
  -6.500  -0.3700   0.03482   0.03136  -0.0575   0.7829   0.0255
  -6.250  -0.3600   0.02853   0.02445  -0.0556   0.7729   0.0281
  -6.000  -0.3381   0.02740   0.02323  -0.0552   0.7587   0.0283
  -5.750  -0.3158   0.02638   0.02208  -0.0548   0.7406   0.0286
  -5.500  -0.2928   0.02532   0.02088  -0.0544   0.7223   0.0289
  -5.250  -0.2745   0.01949   0.01431  -0.0524   0.7114   0.0274
  -5.000  -0.2508   0.01746   0.01196  -0.0517   0.6920   0.0274
  -4.750  -0.2259   0.01586   0.01010  -0.0512   0.6736   0.0273
  -4.500  -0.2000   0.01480   0.00881  -0.0507   0.6526   0.0274
  -4.250  -0.1739   0.01404   0.00784  -0.0503   0.6249   0.0275
  -4.000  -0.1477   0.01362   0.00719  -0.0498   0.5885   0.0277
  -3.750  -0.1227   0.01279   0.00612  -0.0493   0.5392   0.0279
  -3.500  -0.1051   0.01342   0.00571  -0.0479   0.2394   0.0283
  -3.250  -0.0800   0.01333   0.00537  -0.0475   0.1644   0.0287
  -3.000  -0.0540   0.01329   0.00515  -0.0472   0.1092   0.0292
  -2.750  -0.0267   0.01308   0.00492  -0.0470   0.1054   0.0298
  -2.500   0.0004   0.01278   0.00458  -0.0467   0.1039   0.0303
  -2.250   0.0275   0.01252   0.00430  -0.0465   0.1025   0.0307
  -2.000   0.0548   0.01233   0.00406  -0.0463   0.1013   0.0312
  -1.750   0.0823   0.01218   0.00388  -0.0461   0.1003   0.0315
  -1.500   0.1094   0.01194   0.00362  -0.0459   0.0995   0.0319
  -1.250   0.1368   0.01169   0.00336  -0.0458   0.0990   0.0326
  -1.000   0.1646   0.01158   0.00325  -0.0457   0.0985   0.0334
  -0.750   0.1924   0.01150   0.00316  -0.0456   0.0980   0.0342
  -0.500   0.2203   0.01147   0.00311  -0.0455   0.0975   0.0354
  -0.250   0.2482   0.01140   0.00302  -0.0454   0.0971   0.0363
   0.000   0.2761   0.01134   0.00296  -0.0454   0.0967   0.0377
   0.250   0.3039   0.01134   0.00296  -0.0453   0.0962   0.0392
   0.500   0.3318   0.01134   0.00295  -0.0452   0.0959   0.0411
   0.750   0.3596   0.01136   0.00297  -0.0451   0.0956   0.0443
   1.000   0.3873   0.01140   0.00301  -0.0450   0.0951   0.0500
   1.250   0.4145   0.01144   0.00311  -0.0448   0.0942   0.0730
   1.500   0.4406   0.00996   0.00312  -0.0457   0.0935   0.6200
   1.750   0.4682   0.00991   0.00322  -0.0456   0.0929   0.6730
   2.000   0.4957   0.00996   0.00334  -0.0454   0.0924   0.7048
   2.250   0.5231   0.01004   0.00347  -0.0452   0.0920   0.7277
   2.500   0.5504   0.01014   0.00360  -0.0450   0.0913   0.7483
   2.750   0.5778   0.01025   0.00373  -0.0448   0.0906   0.7650
   3.000   0.6046   0.01037   0.00389  -0.0444   0.0899   0.7869
   3.250   0.6312   0.01053   0.00406  -0.0441   0.0892   0.8018
   3.500   0.6574   0.01075   0.00428  -0.0438   0.0887   0.8116
   3.750   0.6845   0.01087   0.00442  -0.0436   0.0882   0.8204
   4.000   0.7121   0.01097   0.00452  -0.0435   0.0877   0.8285
   4.250   0.7390   0.01106   0.00464  -0.0432   0.0871   0.8375
   4.500   0.7662   0.01118   0.00477  -0.0430   0.0864   0.8465
   4.750   0.7927   0.01128   0.00489  -0.0427   0.0856   0.8560
   5.000   0.8194   0.01140   0.00501  -0.0424   0.0848   0.8661
   5.250   0.8453   0.01152   0.00515  -0.0420   0.0840   0.8764
   5.500   0.8717   0.01162   0.00527  -0.0417   0.0830   0.8871
   5.750   0.8972   0.01169   0.00538  -0.0412   0.0820   0.8987
   6.000   0.9227   0.01175   0.00547  -0.0406   0.0806   0.9113
   6.250   0.9475   0.01180   0.00553  -0.0399   0.0790   0.9255
   6.500   0.9706   0.01186   0.00565  -0.0389   0.0770   0.9428
   7.000   1.0239   0.01227   0.00592  -0.0387   0.0524   1.0000
   7.250   1.0487   0.01267   0.00631  -0.0384   0.0503   1.0000
   7.500   1.0742   0.01298   0.00662  -0.0381   0.0484   1.0000
   7.750   1.0986   0.01336   0.00700  -0.0377   0.0467   1.0000
   8.000   1.1243   0.01358   0.00724  -0.0375   0.0445   1.0000
   8.250   1.1495   0.01384   0.00750  -0.0371   0.0418   1.0000
   8.500   1.1738   0.01416   0.00778  -0.0367   0.0373   1.0000
   8.750   1.1972   0.01452   0.00811  -0.0362   0.0358   1.0000
   9.000   1.2201   0.01491   0.00848  -0.0355   0.0348   1.0000
   9.250   1.2427   0.01531   0.00888  -0.0348   0.0342   1.0000
   9.500   1.2647   0.01572   0.00930  -0.0341   0.0337   1.0000
   9.750   1.2857   0.01618   0.00978  -0.0332   0.0330   1.0000
  10.000   1.3056   0.01670   0.01031  -0.0322   0.0324   1.0000
  10.250   1.3247   0.01723   0.01086  -0.0310   0.0319   1.0000
  10.500   1.3423   0.01776   0.01142  -0.0297   0.0316   1.0000
  10.750   1.3587   0.01823   0.01192  -0.0280   0.0314   1.0000
  11.000   1.3738   0.01874   0.01247  -0.0262   0.0312   1.0000
  11.250   1.3882   0.01930   0.01307  -0.0244   0.0310   1.0000
  11.500   1.4021   0.01991   0.01373  -0.0227   0.0308   1.0000
  11.750   1.4156   0.02056   0.01443  -0.0210   0.0306   1.0000
  12.000   1.4283   0.02129   0.01520  -0.0193   0.0304   1.0000
  12.250   1.4401   0.02209   0.01605  -0.0176   0.0302   1.0000
  12.500   1.4512   0.02297   0.01698  -0.0160   0.0300   1.0000
  12.750   1.4618   0.02391   0.01798  -0.0145   0.0298   1.0000
  13.000   1.4705   0.02502   0.01914  -0.0129   0.0296   1.0000
  13.250   1.4769   0.02633   0.02050  -0.0113   0.0293   1.0000
  13.500   1.4812   0.02785   0.02208  -0.0098   0.0291   1.0000
  13.750   1.4826   0.02966   0.02397  -0.0082   0.0288   1.0000
  14.000   1.4908   0.03103   0.02540  -0.0072   0.0288   1.0000
  14.250   1.4987   0.03246   0.02690  -0.0064   0.0286   1.0000
  14.500   1.5054   0.03405   0.02857  -0.0056   0.0285   1.0000
  14.750   1.5113   0.03577   0.03036  -0.0049   0.0284   1.0000
  15.000   1.5157   0.03769   0.03236  -0.0044   0.0282   1.0000
  15.250   1.5190   0.03979   0.03453  -0.0040   0.0280   1.0000
  15.500   1.5214   0.04205   0.03688  -0.0037   0.0278   1.0000
  15.750   1.5225   0.04452   0.03944  -0.0036   0.0277   1.0000
  16.000   1.5224   0.04724   0.04224  -0.0037   0.0275   1.0000
  16.250   1.5214   0.05017   0.04526  -0.0041   0.0274   1.0000
  16.500   1.5187   0.05346   0.04863  -0.0046   0.0272   1.0000
  16.750   1.5153   0.05697   0.05222  -0.0055   0.0270   1.0000
  17.000   1.5104   0.06082   0.05617  -0.0066   0.0269   1.0000
  17.250   1.5042   0.06504   0.06048  -0.0081   0.0268   1.0000
  17.500   1.4968   0.06960   0.06513  -0.0099   0.0267   1.0000
  17.750   1.4873   0.07464   0.07026  -0.0120   0.0265   1.0000
  18.000   1.4770   0.08000   0.07570  -0.0145   0.0264   1.0000
  18.250   1.4663   0.08554   0.08133  -0.0171   0.0263   1.0000
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