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NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il)
Reynolds number: 200,000
Max Cl/Cd: 55.32 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames01-il-200000-n5.txt
Download as CSV file: xf-ames01-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7277   0.06507   0.06155  -0.0217   1.0000   0.0207
  -9.500  -0.7634   0.05562   0.05177  -0.0234   1.0000   0.0207
  -9.250  -0.8094   0.04179   0.03688  -0.0222   1.0000   0.0213
  -9.000  -0.7946   0.04004   0.03502  -0.0219   1.0000   0.0218
  -8.750  -0.7755   0.03898   0.03386  -0.0217   1.0000   0.0224
  -8.500  -0.7595   0.03688   0.03152  -0.0212   1.0000   0.0230
  -8.250  -0.7419   0.03493   0.02934  -0.0208   1.0000   0.0238
  -8.000  -0.7262   0.03211   0.02612  -0.0199   1.0000   0.0250
  -7.750  -0.7108   0.02896   0.02242  -0.0187   1.0000   0.0261
  -7.500  -0.6902   0.02653   0.01949  -0.0180   0.9942   0.0270
  -7.250  -0.6636   0.02489   0.01769  -0.0185   0.9876   0.0278
  -7.000  -0.6345   0.02403   0.01674  -0.0193   0.9828   0.0288
  -6.750  -0.6060   0.02327   0.01586  -0.0199   0.9780   0.0301
  -6.500  -0.5769   0.02226   0.01465  -0.0204   0.9739   0.0318
  -6.250  -0.5490   0.02114   0.01330  -0.0205   0.9693   0.0332
  -6.000  -0.5213   0.02020   0.01217  -0.0206   0.9646   0.0343
  -5.750  -0.4944   0.01925   0.01120  -0.0207   0.9605   0.0359
  -5.500  -0.4678   0.01880   0.01073  -0.0206   0.9557   0.0378
  -5.250  -0.4412   0.01826   0.01012  -0.0204   0.9510   0.0398
  -5.000  -0.4149   0.01767   0.00942  -0.0200   0.9468   0.0417
  -4.750  -0.3886   0.01723   0.00889  -0.0197   0.9422   0.0434
  -4.500  -0.3641   0.01650   0.00820  -0.0191   0.9373   0.0461
  -4.250  -0.3389   0.01609   0.00779  -0.0186   0.9331   0.0486
  -4.000  -0.3132   0.01567   0.00732  -0.0181   0.9284   0.0512
  -3.750  -0.2875   0.01534   0.00693  -0.0176   0.9234   0.0539
  -3.500  -0.2642   0.01489   0.00649  -0.0166   0.9182   0.0574
  -3.250  -0.2397   0.01455   0.00615  -0.0158   0.9104   0.0612
  -3.000  -0.2174   0.01428   0.00583  -0.0143   0.9029   0.0650
  -2.750  -0.1932   0.01395   0.00548  -0.0133   0.8930   0.0700
  -2.500  -0.1697   0.01363   0.00517  -0.0121   0.8846   0.0767
  -2.250  -0.1454   0.01335   0.00485  -0.0111   0.8757   0.0844
  -2.000  -0.1204   0.01300   0.00457  -0.0103   0.8668   0.1006
  -1.750  -0.0974   0.01244   0.00427  -0.0092   0.8586   0.1605
  -1.500  -0.0762   0.01133   0.00399  -0.0083   0.8479   0.3660
  -1.250  -0.0569   0.01038   0.00380  -0.0064   0.8368   0.5605
  -1.000  -0.0383   0.00967   0.00373  -0.0038   0.8247   0.7198
  -0.750  -0.0143   0.00932   0.00378  -0.0017   0.8127   0.8419
  -0.500   0.0260   0.00936   0.00391  -0.0032   0.8007   0.9174
  -0.250   0.0663   0.00947   0.00397  -0.0050   0.7866   0.9550
   0.000   0.1129   0.00958   0.00398  -0.0084   0.7677   0.9769
   0.250   0.1538   0.00961   0.00389  -0.0109   0.7431   0.9876
   0.500   0.1909   0.00963   0.00374  -0.0126   0.7095   0.9949
   0.750   0.2269   0.00970   0.00353  -0.0141   0.6532   1.0000
   1.000   0.2514   0.00992   0.00333  -0.0133   0.5735   1.0000
   1.250   0.2769   0.01035   0.00326  -0.0131   0.4788   1.0000
   1.500   0.3025   0.01082   0.00330  -0.0131   0.3997   1.0000
   1.750   0.3280   0.01118   0.00336  -0.0129   0.3521   1.0000
   2.000   0.3534   0.01146   0.00345  -0.0127   0.3242   1.0000
   2.250   0.3787   0.01168   0.00354  -0.0124   0.3060   1.0000
   2.500   0.4040   0.01190   0.00365  -0.0121   0.2923   1.0000
   2.750   0.4292   0.01211   0.00377  -0.0117   0.2806   1.0000
   3.000   0.4544   0.01231   0.00391  -0.0113   0.2711   1.0000
   3.500   0.5048   0.01274   0.00424  -0.0105   0.2566   1.0000
   3.750   0.5298   0.01298   0.00442  -0.0100   0.2504   1.0000
   4.000   0.5549   0.01322   0.00462  -0.0096   0.2446   1.0000
   4.250   0.5802   0.01344   0.00484  -0.0092   0.2386   1.0000
   4.500   0.6050   0.01372   0.00507  -0.0087   0.2335   1.0000
   4.750   0.6302   0.01397   0.00533  -0.0083   0.2291   1.0000
   5.000   0.6554   0.01421   0.00559  -0.0078   0.2240   1.0000
   5.250   0.6803   0.01451   0.00586  -0.0074   0.2191   1.0000
   5.500   0.7053   0.01481   0.00616  -0.0070   0.2148   1.0000
   5.750   0.7306   0.01506   0.00647  -0.0066   0.2099   1.0000
   6.000   0.7556   0.01535   0.00677  -0.0062   0.2050   1.0000
   6.250   0.7805   0.01569   0.00710  -0.0058   0.2003   1.0000
   6.500   0.8060   0.01593   0.00743  -0.0054   0.1948   1.0000
   6.750   0.8311   0.01622   0.00775  -0.0050   0.1896   1.0000
   7.000   0.8561   0.01653   0.00809  -0.0047   0.1841   1.0000
   7.250   0.8815   0.01677   0.00842  -0.0043   0.1776   1.0000
   7.500   0.9061   0.01710   0.00875  -0.0040   0.1718   1.0000
   7.750   0.9315   0.01735   0.00912  -0.0037   0.1648   1.0000
   8.000   0.9560   0.01765   0.00943  -0.0033   0.1578   1.0000
   8.250   0.9810   0.01791   0.00979  -0.0030   0.1488   1.0000
   8.500   1.0055   0.01824   0.01017  -0.0026   0.1395   1.0000
   8.750   1.0295   0.01861   0.01056  -0.0023   0.1295   1.0000
   9.000   1.0529   0.01905   0.01101  -0.0018   0.1185   1.0000
   9.250   1.0761   0.01954   0.01153  -0.0014   0.1062   1.0000
   9.500   1.0982   0.02015   0.01215  -0.0009   0.0929   1.0000
   9.750   1.1194   0.02087   0.01285  -0.0002   0.0798   1.0000
  10.000   1.1395   0.02171   0.01368   0.0005   0.0685   1.0000
  10.500   1.1773   0.02353   0.01557   0.0022   0.0514   1.0000
  10.750   1.1947   0.02451   0.01662   0.0032   0.0458   1.0000
  11.000   1.2109   0.02555   0.01773   0.0043   0.0413   1.0000
  11.250   1.2249   0.02671   0.01896   0.0056   0.0380   1.0000
  11.500   1.2392   0.02775   0.02014   0.0069   0.0352   1.0000
  11.750   1.2504   0.02896   0.02144   0.0085   0.0328   1.0000
  12.000   1.2549   0.03042   0.02297   0.0107   0.0309   1.0000
  12.250   1.2610   0.03173   0.02444   0.0128   0.0296   1.0000
  12.500   1.2663   0.03321   0.02606   0.0145   0.0283   1.0000
  12.750   1.2698   0.03491   0.02790   0.0161   0.0272   1.0000
  13.000   1.2718   0.03684   0.02996   0.0174   0.0263   1.0000
  13.250   1.2716   0.03908   0.03232   0.0184   0.0255   1.0000
  13.500   1.2685   0.04177   0.03512   0.0191   0.0248   1.0000
  13.750   1.2618   0.04505   0.03853   0.0192   0.0242   1.0000
  14.000   1.2542   0.04873   0.04233   0.0187   0.0237   1.0000
  14.250   1.2491   0.05249   0.04628   0.0177   0.0233   1.0000
  14.500   1.2414   0.05690   0.05087   0.0159   0.0229   1.0000
  14.750   1.2316   0.06203   0.05617   0.0135   0.0226   1.0000
  15.000   1.2198   0.06779   0.06212   0.0104   0.0223   1.0000
  15.250   1.2064   0.07406   0.06854   0.0071   0.0220   1.0000
  15.500   1.1920   0.08057   0.07522   0.0036   0.0218   1.0000
  15.750   1.1774   0.08714   0.08192   0.0003   0.0216   1.0000
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