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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 500,000
Max Cl/Cd: 95.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40-il-500000.txt
Download as CSV file: xf-usa40-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3106   0.09682   0.09440  -0.0401   1.0000   0.0427
  -9.500  -0.3092   0.09407   0.09168  -0.0405   1.0000   0.0436
  -9.250  -0.5152   0.03184   0.02795  -0.1014   0.9828   0.0359
  -9.000  -0.4903   0.02820   0.02391  -0.1046   0.9771   0.0359
  -8.750  -0.4585   0.02596   0.02149  -0.1074   0.9739   0.0363
  -8.500  -0.4232   0.02471   0.02019  -0.1100   0.9719   0.0368
  -8.250  -0.3870   0.02316   0.01850  -0.1128   0.9702   0.0373
  -8.000  -0.3587   0.02139   0.01649  -0.1139   0.9637   0.0375
  -7.750  -0.3252   0.01985   0.01475  -0.1157   0.9590   0.0378
  -7.500  -0.2934   0.01855   0.01328  -0.1169   0.9524   0.0382
  -7.250  -0.2633   0.01746   0.01204  -0.1175   0.9435   0.0386
  -7.000  -0.2344   0.01653   0.01097  -0.1178   0.9343   0.0391
  -6.750  -0.2046   0.01570   0.01001  -0.1181   0.9257   0.0396
  -6.500  -0.1773   0.01505   0.00924  -0.1180   0.9146   0.0401
  -6.250  -0.1486   0.01460   0.00866  -0.1179   0.9043   0.0406
  -6.000  -0.1221   0.01359   0.00760  -0.1177   0.8926   0.0415
  -5.750  -0.0950   0.01306   0.00703  -0.1175   0.8803   0.0422
  -5.500  -0.0675   0.01263   0.00656  -0.1173   0.8682   0.0429
  -5.250  -0.0399   0.01226   0.00611  -0.1170   0.8554   0.0438
  -5.000  -0.0125   0.01190   0.00568  -0.1168   0.8417   0.0447
  -4.750   0.0152   0.01159   0.00529  -0.1165   0.8281   0.0457
  -4.500   0.0427   0.01123   0.00485  -0.1163   0.8139   0.0468
  -4.250   0.0702   0.01086   0.00444  -0.1161   0.7993   0.0485
  -4.000   0.0980   0.01067   0.00419  -0.1159   0.7842   0.0505
  -3.750   0.1258   0.01052   0.00395  -0.1157   0.7683   0.0527
  -3.500   0.1535   0.01023   0.00363  -0.1155   0.7521   0.0559
  -3.250   0.1814   0.01010   0.00343  -0.1153   0.7361   0.0598
  -3.000   0.2093   0.00989   0.00319  -0.1152   0.7205   0.0664
  -2.750   0.2372   0.00971   0.00298  -0.1150   0.7047   0.0767
  -2.500   0.2650   0.00956   0.00279  -0.1149   0.6893   0.0898
  -2.250   0.2929   0.00939   0.00263  -0.1148   0.6748   0.1086
  -2.000   0.3207   0.00916   0.00254  -0.1148   0.6604   0.1585
  -1.750   0.3487   0.00905   0.00251  -0.1147   0.6461   0.2025
  -1.500   0.3767   0.00900   0.00247  -0.1146   0.6321   0.2300
  -1.250   0.4046   0.00893   0.00243  -0.1146   0.6186   0.2595
  -1.000   0.4323   0.00884   0.00241  -0.1145   0.6046   0.3052
  -0.750   0.4603   0.00867   0.00243  -0.1145   0.5897   0.3824
  -0.500   0.4880   0.00850   0.00246  -0.1145   0.5742   0.4609
  -0.250   0.5153   0.00838   0.00252  -0.1143   0.5575   0.5438
   0.000   0.5422   0.00837   0.00262  -0.1140   0.5388   0.6150
   0.250   0.5689   0.00846   0.00271  -0.1135   0.5181   0.6585
   0.500   0.5955   0.00861   0.00279  -0.1130   0.4971   0.6874
   0.750   0.6222   0.00877   0.00290  -0.1126   0.4778   0.7151
   1.000   0.6490   0.00895   0.00300  -0.1122   0.4611   0.7347
   1.500   0.7025   0.00927   0.00323  -0.1114   0.4336   0.7692
   1.750   0.7292   0.00941   0.00333  -0.1110   0.4215   0.7823
   2.000   0.7557   0.00959   0.00345  -0.1105   0.4094   0.7942
   2.250   0.7824   0.00973   0.00355  -0.1102   0.3973   0.8078
   2.500   0.8091   0.00986   0.00366  -0.1098   0.3866   0.8220
   3.000   0.8616   0.01008   0.00387  -0.1089   0.3672   0.8491
   3.250   0.8872   0.01022   0.00398  -0.1083   0.3581   0.8645
   3.500   0.9127   0.01024   0.00407  -0.1077   0.3499   0.8869
   3.750   0.9391   0.01025   0.00414  -0.1072   0.3407   1.0000
   4.000   0.9674   0.01043   0.00426  -0.1073   0.3307   1.0000
   4.250   0.9949   0.01065   0.00442  -0.1073   0.3218   1.0000
   4.500   1.0222   0.01087   0.00458  -0.1073   0.3117   1.0000
   4.750   1.0494   0.01109   0.00474  -0.1072   0.3018   1.0000
   5.000   1.0758   0.01136   0.00493  -0.1069   0.2915   1.0000
   5.250   1.1028   0.01157   0.00511  -0.1068   0.2813   1.0000
   5.500   1.1290   0.01183   0.00532  -0.1066   0.2710   1.0000
   5.750   1.1546   0.01214   0.00554  -0.1062   0.2578   1.0000
   6.000   1.1798   0.01247   0.00579  -0.1058   0.2437   1.0000
   6.250   1.2045   0.01284   0.00606  -0.1054   0.2269   1.0000
   6.500   1.2281   0.01330   0.00638  -0.1048   0.2057   1.0000
   6.750   1.2502   0.01388   0.00680  -0.1040   0.1810   1.0000
   7.000   1.2702   0.01464   0.00734  -0.1029   0.1487   1.0000
   7.250   1.2820   0.01610   0.00839  -0.1008   0.0915   1.0000
   7.500   1.3030   0.01669   0.00892  -0.0998   0.0820   1.0000
   7.750   1.3245   0.01720   0.00941  -0.0989   0.0761   1.0000
   8.000   1.3458   0.01770   0.00988  -0.0979   0.0690   1.0000
   8.250   1.3619   0.01859   0.01061  -0.0963   0.0413   1.0000
   8.500   1.3797   0.01928   0.01129  -0.0949   0.0377   1.0000
   8.750   1.3984   0.01985   0.01189  -0.0935   0.0365   1.0000
   9.000   1.4148   0.02044   0.01254  -0.0918   0.0357   1.0000
   9.250   1.4302   0.02111   0.01326  -0.0900   0.0350   1.0000
   9.500   1.4442   0.02185   0.01407  -0.0881   0.0343   1.0000
   9.750   1.4566   0.02271   0.01499  -0.0861   0.0336   1.0000
  10.000   1.4672   0.02370   0.01605  -0.0839   0.0329   1.0000
  10.250   1.4791   0.02462   0.01704  -0.0821   0.0326   1.0000
  10.500   1.4897   0.02567   0.01816  -0.0802   0.0322   1.0000
  10.750   1.4985   0.02688   0.01945  -0.0784   0.0319   1.0000
  11.000   1.5060   0.02826   0.02090  -0.0766   0.0315   1.0000
  11.250   1.5117   0.02985   0.02257  -0.0749   0.0312   1.0000
  11.500   1.5158   0.03167   0.02448  -0.0733   0.0309   1.0000
  11.750   1.5179   0.03377   0.02667  -0.0719   0.0306   1.0000
  12.000   1.5178   0.03622   0.02921  -0.0707   0.0302   1.0000
  12.250   1.5153   0.03905   0.03213  -0.0697   0.0299   1.0000
  12.500   1.5100   0.04236   0.03554  -0.0690   0.0296   1.0000
  12.750   1.5024   0.04608   0.03937  -0.0687   0.0294   1.0000
  13.000   1.4922   0.05030   0.04369  -0.0686   0.0291   1.0000
  13.250   1.4808   0.05474   0.04824  -0.0687   0.0290   1.0000
  13.500   1.4693   0.05930   0.05289  -0.0690   0.0288   1.0000
  13.750   1.4670   0.06285   0.05655  -0.0693   0.0287   1.0000
  14.000   1.4637   0.06658   0.06036  -0.0697   0.0285   1.0000
  14.250   1.4599   0.07042   0.06430  -0.0702   0.0284   1.0000
  14.500   1.4560   0.07432   0.06828  -0.0707   0.0282   1.0000
  14.750   1.4522   0.07822   0.07226  -0.0713   0.0281   1.0000
  15.000   1.4487   0.08208   0.07620  -0.0718   0.0279   1.0000
  15.250   1.4460   0.08585   0.08003  -0.0724   0.0276   1.0000
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