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NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.47 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames01-il-1000000-n5.txt
Download as CSV file: xf-ames01-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-01 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.3252   0.05356   0.05083  -0.0221   1.0000   0.0036
 -15.750  -1.3570   0.04621   0.04323  -0.0258   1.0000   0.0036
 -15.500  -1.3739   0.04194   0.03876  -0.0259   1.0000   0.0036
 -15.250  -1.3855   0.03876   0.03541  -0.0245   1.0000   0.0036
 -15.000  -1.3920   0.03635   0.03283  -0.0222   1.0000   0.0036
 -14.750  -1.3954   0.03437   0.03070  -0.0192   1.0000   0.0036
 -14.500  -1.3909   0.03259   0.02878  -0.0171   1.0000   0.0037
 -14.250  -1.3819   0.03095   0.02700  -0.0155   1.0000   0.0037
 -14.000  -1.3696   0.02949   0.02539  -0.0142   1.0000   0.0038
 -13.750  -1.3551   0.02816   0.02393  -0.0130   0.9829   0.0039
 -13.500  -1.3414   0.02704   0.02267  -0.0114   0.9636   0.0039
 -13.250  -1.3265   0.02600   0.02149  -0.0098   0.9548   0.0040
 -13.000  -1.3101   0.02502   0.02038  -0.0083   0.9485   0.0040
 -12.750  -1.2925   0.02400   0.01924  -0.0071   0.9438   0.0042
 -12.500  -1.2735   0.02305   0.01819  -0.0061   0.9395   0.0043
 -12.250  -1.2540   0.02216   0.01719  -0.0050   0.9352   0.0045
 -12.000  -1.2338   0.02134   0.01625  -0.0040   0.9315   0.0047
 -11.750  -1.2121   0.02055   0.01537  -0.0033   0.9280   0.0049
 -11.500  -1.1899   0.01982   0.01456  -0.0026   0.9246   0.0051
 -11.250  -1.1674   0.01915   0.01381  -0.0018   0.9215   0.0054
 -11.000  -1.1446   0.01852   0.01309  -0.0011   0.9185   0.0057
 -10.750  -1.1210   0.01789   0.01240  -0.0006   0.9156   0.0062
 -10.500  -1.0968   0.01731   0.01175  -0.0001   0.9125   0.0067
 -10.250  -1.0723   0.01679   0.01116   0.0004   0.9096   0.0073
 -10.000  -1.0476   0.01631   0.01062   0.0008   0.9068   0.0076
  -9.750  -1.0229   0.01585   0.01010   0.0013   0.9041   0.0080
  -9.500  -0.9975   0.01538   0.00959   0.0017   0.9014   0.0085
  -9.250  -0.9716   0.01496   0.00913   0.0020   0.8987   0.0090
  -9.000  -0.9456   0.01456   0.00867   0.0022   0.8958   0.0094
  -8.750  -0.9196   0.01419   0.00825   0.0025   0.8929   0.0099
  -8.500  -0.8934   0.01384   0.00786   0.0029   0.8903   0.0102
  -8.250  -0.8672   0.01350   0.00747   0.0031   0.8879   0.0106
  -8.000  -0.8404   0.01314   0.00710   0.0033   0.8852   0.0112
  -7.750  -0.8134   0.01282   0.00675   0.0034   0.8822   0.0119
  -7.500  -0.7865   0.01252   0.00642   0.0036   0.8794   0.0125
  -7.250  -0.7595   0.01223   0.00610   0.0038   0.8766   0.0129
  -7.000  -0.7325   0.01196   0.00580   0.0040   0.8740   0.0136
  -6.750  -0.7051   0.01168   0.00552   0.0041   0.8714   0.0147
  -6.500  -0.6774   0.01143   0.00526   0.0041   0.8684   0.0157
  -6.250  -0.6497   0.01119   0.00500   0.0041   0.8654   0.0166
  -6.000  -0.6221   0.01096   0.00475   0.0042   0.8624   0.0175
  -5.750  -0.5945   0.01073   0.00451   0.0043   0.8596   0.0185
  -5.500  -0.5666   0.01052   0.00429   0.0044   0.8568   0.0196
  -5.250  -0.5384   0.01031   0.00408   0.0043   0.8524   0.0206
  -5.000  -0.5105   0.01012   0.00387   0.0044   0.8472   0.0216
  -4.750  -0.4827   0.00992   0.00366   0.0045   0.8421   0.0232
  -4.500  -0.4544   0.00974   0.00348   0.0045   0.8355   0.0249
  -4.250  -0.4264   0.00957   0.00329   0.0045   0.8289   0.0260
  -4.000  -0.3979   0.00942   0.00312   0.0045   0.8225   0.0271
  -3.750  -0.3697   0.00925   0.00295   0.0045   0.8144   0.0295
  -3.500  -0.3412   0.00910   0.00280   0.0045   0.8055   0.0318
  -3.250  -0.3128   0.00900   0.00267   0.0044   0.7960   0.0340
  -3.000  -0.2842   0.00884   0.00253   0.0044   0.7854   0.0378
  -2.750  -0.2556   0.00872   0.00239   0.0043   0.7732   0.0406
  -2.500  -0.2269   0.00863   0.00225   0.0042   0.7579   0.0424
  -2.250  -0.1981   0.00856   0.00211   0.0041   0.7362   0.0439
  -2.000  -0.1694   0.00850   0.00197   0.0040   0.7074   0.0478
  -1.750  -0.1404   0.00847   0.00186   0.0038   0.6756   0.0518
  -1.500  -0.1113   0.00850   0.00177   0.0035   0.6397   0.0548
  -1.250  -0.0822   0.00855   0.00170   0.0032   0.5934   0.0622
  -1.000  -0.0530   0.00866   0.00165   0.0028   0.5375   0.0720
  -0.750  -0.0240   0.00882   0.00162   0.0024   0.4659   0.0905
  -0.500   0.0045   0.00889   0.00160   0.0019   0.3943   0.1401
  -0.250   0.0321   0.00865   0.00155   0.0016   0.3465   0.2515
   0.000   0.0593   0.00833   0.00151   0.0014   0.3123   0.3798
   0.250   0.0860   0.00793   0.00148   0.0013   0.2883   0.5219
   0.500   0.1126   0.00757   0.00149   0.0014   0.2722   0.6480
   0.750   0.1394   0.00734   0.00151   0.0016   0.2604   0.7349
   1.000   0.1648   0.00710   0.00156   0.0022   0.2496   0.8274
   1.250   0.1898   0.00698   0.00163   0.0031   0.2415   0.8952
   1.500   0.2161   0.00701   0.00172   0.0038   0.2333   0.9424
   1.750   0.2473   0.00710   0.00180   0.0033   0.2280   0.9651
   2.000   0.2788   0.00720   0.00186   0.0025   0.2225   0.9737
   2.250   0.3112   0.00733   0.00193   0.0015   0.2170   0.9804
   2.500   0.3432   0.00742   0.00200   0.0007   0.2132   0.9850
   2.750   0.3769   0.00753   0.00207  -0.0006   0.2082   0.9872
   3.000   0.4104   0.00766   0.00215  -0.0019   0.2034   0.9893
   3.250   0.4434   0.00777   0.00224  -0.0031   0.2003   0.9914
   3.500   0.4758   0.00787   0.00233  -0.0041   0.1972   0.9936
   3.750   0.5086   0.00799   0.00242  -0.0052   0.1929   0.9951
   4.000   0.5421   0.00813   0.00252  -0.0066   0.1882   0.9963
   4.250   0.5754   0.00824   0.00263  -0.0078   0.1853   0.9977
   4.500   0.6085   0.00835   0.00274  -0.0090   0.1817   0.9991
   4.750   0.6401   0.00849   0.00285  -0.0099   0.1767   1.0000
   5.000   0.6660   0.00863   0.00296  -0.0096   0.1721   1.0000
   5.250   0.6920   0.00873   0.00307  -0.0092   0.1687   1.0000
   5.500   0.7179   0.00886   0.00318  -0.0089   0.1635   1.0000
   5.750   0.7439   0.00902   0.00331  -0.0086   0.1573   1.0000
   6.000   0.7700   0.00915   0.00344  -0.0083   0.1530   1.0000
   6.250   0.7960   0.00932   0.00358  -0.0080   0.1469   1.0000
   6.500   0.8221   0.00949   0.00374  -0.0078   0.1408   1.0000
   6.750   0.8478   0.00973   0.00392  -0.0075   0.1307   1.0000
   7.000   0.8738   0.00993   0.00411  -0.0073   0.1236   1.0000
   7.250   0.8997   0.01017   0.00431  -0.0070   0.1155   1.0000
   7.500   0.9253   0.01048   0.00456  -0.0068   0.1040   1.0000
   7.750   0.9507   0.01083   0.00484  -0.0065   0.0914   1.0000
   8.000   0.9759   0.01122   0.00516  -0.0063   0.0786   1.0000
   8.250   1.0010   0.01162   0.00551  -0.0061   0.0679   1.0000
   8.500   1.0261   0.01204   0.00589  -0.0058   0.0582   1.0000
   8.750   1.0511   0.01246   0.00626  -0.0056   0.0501   1.0000
   9.000   1.0761   0.01286   0.00664  -0.0054   0.0432   1.0000
   9.250   1.1009   0.01331   0.00707  -0.0051   0.0369   1.0000
   9.500   1.1253   0.01378   0.00751  -0.0048   0.0314   1.0000
   9.750   1.1500   0.01419   0.00792  -0.0046   0.0277   1.0000
  10.000   1.1741   0.01468   0.00840  -0.0043   0.0238   1.0000
  10.250   1.1985   0.01510   0.00884  -0.0040   0.0218   1.0000
  10.500   1.2223   0.01558   0.00933  -0.0036   0.0198   1.0000
  10.750   1.2459   0.01606   0.00982  -0.0033   0.0181   1.0000
  11.000   1.2696   0.01650   0.01030  -0.0029   0.0171   1.0000
  11.250   1.2925   0.01700   0.01083  -0.0025   0.0159   1.0000
  11.500   1.3147   0.01757   0.01142  -0.0020   0.0146   1.0000
  11.750   1.3367   0.01811   0.01200  -0.0014   0.0137   1.0000
  12.000   1.3588   0.01862   0.01255  -0.0009   0.0130   1.0000
  12.250   1.3799   0.01918   0.01315  -0.0003   0.0122   1.0000
  12.500   1.4001   0.01980   0.01381   0.0004   0.0114   1.0000
  12.750   1.4192   0.02048   0.01453   0.0012   0.0107   1.0000
  13.000   1.4378   0.02116   0.01526   0.0021   0.0102   1.0000
  13.250   1.4561   0.02180   0.01597   0.0030   0.0100   1.0000
  13.500   1.4730   0.02250   0.01673   0.0041   0.0097   1.0000
  13.750   1.4878   0.02324   0.01754   0.0055   0.0094   1.0000
  14.000   1.4987   0.02406   0.01842   0.0073   0.0091   1.0000
  14.250   1.5088   0.02499   0.01942   0.0091   0.0088   1.0000
  14.500   1.5184   0.02603   0.02052   0.0106   0.0086   1.0000
  14.750   1.5271   0.02719   0.02176   0.0121   0.0083   1.0000
  15.000   1.5347   0.02851   0.02315   0.0135   0.0081   1.0000
  15.250   1.5408   0.02999   0.02471   0.0147   0.0078   1.0000
  15.500   1.5450   0.03171   0.02652   0.0159   0.0076   1.0000
  15.750   1.5494   0.03350   0.02840   0.0168   0.0075   1.0000
  16.000   1.5528   0.03547   0.03047   0.0174   0.0074   1.0000
  16.250   1.5542   0.03775   0.03286   0.0178   0.0073   1.0000
  16.500   1.5537   0.04040   0.03562   0.0179   0.0072   1.0000
  16.750   1.5502   0.04356   0.03890   0.0175   0.0071   1.0000
  17.000   1.5435   0.04741   0.04287   0.0165   0.0071   1.0000
  17.250   1.5325   0.05219   0.04780   0.0147   0.0070   1.0000
  17.500   1.5151   0.05845   0.05423   0.0116   0.0070   1.0000
  17.750   1.4872   0.06713   0.06310   0.0068   0.0070   1.0000
  18.000   1.4425   0.07923   0.07545   0.0003   0.0071   1.0000
  18.250   1.3840   0.09326   0.08970  -0.0066   0.0072   1.0000
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