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NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.82 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames02-il-1000000-n5.txt
Download as CSV file: xf-ames02-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-02 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -1.2404   0.05249   0.05018  -0.0040   1.0000   0.0057
 -13.250  -1.2699   0.04513   0.04256  -0.0086   1.0000   0.0056
 -13.000  -1.2906   0.04094   0.03815  -0.0071   1.0000   0.0056
 -12.750  -1.2960   0.03731   0.03427  -0.0061   1.0000   0.0057
 -12.500  -1.2923   0.03440   0.03113  -0.0051   1.0000   0.0058
 -12.250  -1.2823   0.03211   0.02863  -0.0042   1.0000   0.0058
 -12.000  -1.2685   0.03018   0.02654  -0.0035   1.0000   0.0059
 -11.750  -1.2519   0.02856   0.02476  -0.0028   1.0000   0.0060
 -11.500  -1.2334   0.02715   0.02321  -0.0022   1.0000   0.0060
 -11.250  -1.2136   0.02587   0.02178  -0.0017   1.0000   0.0061
 -11.000  -1.1928   0.02466   0.02044  -0.0013   1.0000   0.0062
 -10.750  -1.1711   0.02356   0.01920  -0.0009   1.0000   0.0063
 -10.500  -1.1486   0.02252   0.01805  -0.0005   1.0000   0.0064
 -10.250  -1.1255   0.02154   0.01694  -0.0001   1.0000   0.0065
 -10.000  -1.1019   0.02059   0.01588   0.0002   1.0000   0.0067
  -9.750  -1.0778   0.01971   0.01488   0.0004   1.0000   0.0068
  -9.500  -1.0533   0.01886   0.01390   0.0007   1.0000   0.0070
  -9.250  -1.0281   0.01810   0.01305   0.0009   1.0000   0.0071
  -9.000  -1.0025   0.01743   0.01227   0.0011   1.0000   0.0073
  -8.750  -0.9765   0.01683   0.01158   0.0012   1.0000   0.0075
  -8.500  -0.9505   0.01615   0.01081   0.0013   1.0000   0.0076
  -8.250  -0.9245   0.01543   0.01003   0.0014   1.0000   0.0079
  -8.000  -0.8978   0.01489   0.00944   0.0015   1.0000   0.0081
  -7.750  -0.8708   0.01439   0.00889   0.0015   1.0000   0.0083
  -7.500  -0.8435   0.01393   0.00838   0.0015   1.0000   0.0085
  -7.250  -0.8162   0.01346   0.00786   0.0016   1.0000   0.0087
  -7.000  -0.7886   0.01301   0.00737   0.0015   1.0000   0.0090
  -6.750  -0.7609   0.01258   0.00689   0.0015   1.0000   0.0093
  -6.500  -0.7330   0.01217   0.00644   0.0014   1.0000   0.0095
  -6.250  -0.7048   0.01181   0.00603   0.0013   1.0000   0.0097
  -6.000  -0.6768   0.01133   0.00554   0.0012   1.0000   0.0101
  -5.750  -0.6484   0.01098   0.00518   0.0011   1.0000   0.0105
  -5.250  -0.5907   0.01046   0.00461   0.0007   0.9700   0.0115
  -5.000  -0.5643   0.01027   0.00438   0.0012   0.9566   0.0120
  -4.750  -0.5384   0.01002   0.00410   0.0017   0.9462   0.0127
  -4.500  -0.5115   0.00981   0.00388   0.0020   0.9374   0.0133
  -4.250  -0.4845   0.00961   0.00365   0.0024   0.9298   0.0140
  -4.000  -0.4571   0.00941   0.00342   0.0026   0.9221   0.0148
  -3.750  -0.4297   0.00922   0.00322   0.0028   0.9150   0.0158
  -3.500  -0.4018   0.00905   0.00304   0.0030   0.9074   0.0170
  -3.250  -0.3742   0.00888   0.00286   0.0032   0.9002   0.0188
  -3.000  -0.3459   0.00871   0.00269   0.0032   0.8923   0.0210
  -2.500  -0.2896   0.00842   0.00239   0.0034   0.8760   0.0275
  -2.250  -0.2616   0.00828   0.00226   0.0035   0.8659   0.0330
  -2.000  -0.2334   0.00814   0.00213   0.0036   0.8515   0.0419
  -1.750  -0.2053   0.00800   0.00199   0.0037   0.8318   0.0539
  -1.500  -0.1771   0.00786   0.00186   0.0037   0.8088   0.0739
  -1.250  -0.1487   0.00767   0.00174   0.0037   0.7864   0.1091
  -1.000  -0.1201   0.00741   0.00163   0.0035   0.7655   0.1660
  -0.750  -0.0916   0.00715   0.00151   0.0033   0.7353   0.2397
  -0.500  -0.0629   0.00684   0.00141   0.0030   0.7005   0.3366
  -0.250  -0.0344   0.00647   0.00133   0.0027   0.6594   0.4621
   0.000  -0.0056   0.00633   0.00130   0.0024   0.6054   0.5505
   0.250   0.0231   0.00630   0.00131   0.0021   0.5410   0.6254
   0.500   0.0520   0.00642   0.00134   0.0018   0.4698   0.6767
   0.750   0.0807   0.00656   0.00139   0.0015   0.4004   0.7222
   1.000   0.1091   0.00669   0.00145   0.0014   0.3366   0.7673
   1.250   0.1376   0.00683   0.00151   0.0012   0.2841   0.7982
   1.500   0.1661   0.00697   0.00156   0.0011   0.2426   0.8198
   1.750   0.1942   0.00707   0.00162   0.0011   0.2090   0.8454
   2.000   0.2213   0.00713   0.00169   0.0014   0.1812   0.8790
   2.250   0.2466   0.00716   0.00175   0.0022   0.1576   0.9232
   2.500   0.2749   0.00722   0.00178   0.0023   0.1361   0.9712
   2.750   0.3075   0.00736   0.00183   0.0013   0.1177   1.0000
   3.000   0.3364   0.00756   0.00194   0.0011   0.1020   1.0000
   3.250   0.3653   0.00774   0.00205   0.0009   0.0895   1.0000
   3.500   0.3942   0.00793   0.00217   0.0007   0.0783   1.0000
   3.750   0.4230   0.00812   0.00230   0.0005   0.0689   1.0000
   4.000   0.4518   0.00832   0.00244   0.0003   0.0606   1.0000
   4.250   0.4805   0.00852   0.00260   0.0001   0.0533   1.0000
   4.500   0.5092   0.00872   0.00276   0.0000   0.0473   1.0000
   4.750   0.5379   0.00893   0.00293  -0.0002   0.0426   1.0000
   5.000   0.5665   0.00914   0.00311  -0.0004   0.0387   1.0000
   5.250   0.5950   0.00936   0.00331  -0.0005   0.0351   1.0000
   5.500   0.6234   0.00958   0.00352  -0.0007   0.0318   1.0000
   5.750   0.6518   0.00983   0.00374  -0.0008   0.0291   1.0000
   6.000   0.6802   0.01006   0.00397  -0.0009   0.0269   1.0000
   6.250   0.7084   0.01031   0.00422  -0.0010   0.0250   1.0000
   6.500   0.7365   0.01059   0.00448  -0.0012   0.0231   1.0000
   6.750   0.7646   0.01085   0.00476  -0.0013   0.0215   1.0000
   7.000   0.7925   0.01116   0.00505  -0.0014   0.0201   1.0000
   7.250   0.8204   0.01144   0.00536  -0.0015   0.0190   1.0000
   7.500   0.8482   0.01175   0.00568  -0.0015   0.0180   1.0000
   7.750   0.8757   0.01211   0.00604  -0.0016   0.0171   1.0000
   8.000   0.9033   0.01243   0.00640  -0.0017   0.0164   1.0000
   8.250   0.9307   0.01278   0.00678  -0.0017   0.0158   1.0000
   8.500   0.9579   0.01316   0.00718  -0.0017   0.0151   1.0000
   8.750   0.9848   0.01360   0.00764  -0.0017   0.0145   1.0000
   9.000   1.0117   0.01398   0.00807  -0.0017   0.0141   1.0000
   9.250   1.0385   0.01438   0.00851  -0.0017   0.0136   1.0000
   9.500   1.0650   0.01482   0.00898  -0.0017   0.0132   1.0000
   9.750   1.0913   0.01529   0.00949  -0.0017   0.0128   1.0000
  10.000   1.1171   0.01584   0.01009  -0.0016   0.0124   1.0000
  10.250   1.1427   0.01641   0.01071  -0.0015   0.0121   1.0000
  10.500   1.1683   0.01692   0.01129  -0.0014   0.0119   1.0000
  10.750   1.1937   0.01743   0.01187  -0.0012   0.0115   1.0000
  11.000   1.2189   0.01794   0.01244  -0.0011   0.0111   1.0000
  11.250   1.2439   0.01847   0.01302  -0.0010   0.0107   1.0000
  11.500   1.2682   0.01909   0.01368  -0.0008   0.0104   1.0000
  11.750   1.2915   0.01985   0.01450  -0.0005   0.0100   1.0000
  12.000   1.3153   0.02048   0.01521  -0.0002   0.0098   1.0000
  12.250   1.3384   0.02117   0.01599   0.0001   0.0096   1.0000
  12.500   1.3610   0.02191   0.01683   0.0004   0.0094   1.0000
  12.750   1.3831   0.02267   0.01768   0.0008   0.0092   1.0000
  13.000   1.4046   0.02345   0.01854   0.0012   0.0090   1.0000
  13.250   1.4255   0.02427   0.01945   0.0017   0.0088   1.0000
  13.500   1.4456   0.02515   0.02041   0.0023   0.0086   1.0000
  13.750   1.4646   0.02610   0.02144   0.0029   0.0084   1.0000
  14.000   1.4821   0.02718   0.02262   0.0036   0.0082   1.0000
  14.250   1.4976   0.02840   0.02394   0.0044   0.0081   1.0000
  14.500   1.5108   0.02977   0.02542   0.0054   0.0079   1.0000
  14.750   1.5235   0.03105   0.02682   0.0065   0.0079   1.0000
  15.000   1.5332   0.03246   0.02836   0.0078   0.0078   1.0000
  15.250   1.5371   0.03402   0.03004   0.0096   0.0077   1.0000
  15.500   1.5347   0.03597   0.03213   0.0115   0.0076   1.0000
  15.750   1.5306   0.03851   0.03481   0.0124   0.0076   1.0000
  16.000   1.5240   0.04177   0.03822   0.0122   0.0075   1.0000
  16.250   1.5135   0.04612   0.04274   0.0105   0.0075   1.0000
  16.500   1.4931   0.05298   0.04981   0.0060   0.0075   1.0000
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