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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 500,000
Max Cl/Cd: 82.19 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40-il-500000-n5.txt
Download as CSV file: xf-usa40-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7565   0.04095   0.03753  -0.0834   1.0000   0.0254
 -11.750  -0.7645   0.03533   0.03162  -0.0913   0.9962   0.0255
 -11.500  -0.7434   0.03165   0.02762  -0.0973   0.9909   0.0257
 -11.250  -0.7193   0.02906   0.02478  -0.1009   0.9861   0.0259
 -11.000  -0.6913   0.02698   0.02246  -0.1041   0.9830   0.0261
 -10.750  -0.6654   0.02535   0.02062  -0.1059   0.9779   0.0263
 -10.500  -0.6367   0.02393   0.01902  -0.1078   0.9735   0.0265
 -10.250  -0.6060   0.02270   0.01761  -0.1097   0.9702   0.0266
 -10.000  -0.5807   0.02142   0.01620  -0.1104   0.9634   0.0268
  -9.750  -0.5512   0.02025   0.01493  -0.1118   0.9586   0.0271
  -9.500  -0.5224   0.01935   0.01396  -0.1127   0.9526   0.0273
  -9.250  -0.4932   0.01857   0.01311  -0.1136   0.9458   0.0276
  -9.000  -0.4628   0.01785   0.01232  -0.1145   0.9399   0.0278
  -8.750  -0.4345   0.01724   0.01164  -0.1150   0.9319   0.0282
  -8.250  -0.3767   0.01609   0.01034  -0.1158   0.9149   0.0289
  -8.000  -0.3481   0.01553   0.00968  -0.1161   0.9055   0.0293
  -7.750  -0.3206   0.01501   0.00906  -0.1162   0.8929   0.0296
  -7.500  -0.2933   0.01453   0.00847  -0.1161   0.8772   0.0299
  -7.250  -0.2662   0.01411   0.00793  -0.1159   0.8603   0.0302
  -7.000  -0.2390   0.01372   0.00742  -0.1157   0.8449   0.0305
  -6.750  -0.2116   0.01337   0.00696  -0.1156   0.8311   0.0308
  -6.500  -0.1844   0.01297   0.00647  -0.1155   0.8165   0.0311
  -6.250  -0.1571   0.01257   0.00601  -0.1154   0.8013   0.0316
  -6.000  -0.1297   0.01226   0.00563  -0.1153   0.7858   0.0321
  -5.750  -0.1021   0.01200   0.00529  -0.1151   0.7701   0.0326
  -5.500  -0.0745   0.01177   0.00497  -0.1150   0.7537   0.0331
  -5.250  -0.0469   0.01157   0.00468  -0.1148   0.7370   0.0338
  -5.000  -0.0193   0.01139   0.00440  -0.1147   0.7203   0.0346
  -4.750   0.0085   0.01124   0.00415  -0.1145   0.7040   0.0353
  -4.500   0.0361   0.01106   0.00389  -0.1144   0.6874   0.0363
  -4.250   0.0639   0.01090   0.00366  -0.1142   0.6719   0.0374
  -4.000   0.0920   0.01077   0.00346  -0.1142   0.6581   0.0386
  -3.750   0.1200   0.01066   0.00328  -0.1140   0.6447   0.0400
  -3.500   0.1480   0.01056   0.00311  -0.1139   0.6315   0.0419
  -3.250   0.1762   0.01045   0.00297  -0.1139   0.6186   0.0447
  -3.000   0.2045   0.01036   0.00285  -0.1138   0.6074   0.0488
  -2.750   0.2325   0.01029   0.00275  -0.1137   0.5950   0.0552
  -2.500   0.2608   0.01022   0.00267  -0.1137   0.5816   0.0635
  -2.250   0.2890   0.01016   0.00259  -0.1136   0.5687   0.0717
  -2.000   0.3171   0.01013   0.00251  -0.1135   0.5556   0.0794
  -1.750   0.3451   0.01009   0.00244  -0.1135   0.5405   0.0885
  -1.500   0.3731   0.01005   0.00238  -0.1134   0.5235   0.1019
  -1.250   0.4010   0.00994   0.00234  -0.1134   0.5062   0.1384
  -1.000   0.4288   0.00990   0.00235  -0.1134   0.4897   0.1801
  -0.750   0.4564   0.00992   0.00236  -0.1133   0.4713   0.2056
  -0.500   0.4837   0.00997   0.00238  -0.1131   0.4517   0.2320
   0.000   0.5389   0.00993   0.00247  -0.1131   0.4185   0.3247
   0.250   0.5667   0.00990   0.00253  -0.1131   0.4063   0.3824
   0.500   0.5944   0.00993   0.00260  -0.1130   0.3950   0.4224
   0.750   0.6224   0.00988   0.00268  -0.1130   0.3850   0.4848
   1.000   0.6500   0.00985   0.00280  -0.1130   0.3756   0.5531
   1.250   0.6774   0.00992   0.00292  -0.1128   0.3642   0.5995
   1.500   0.7047   0.01000   0.00306  -0.1125   0.3537   0.6417
   1.750   0.7316   0.01014   0.00320  -0.1122   0.3424   0.6741
   2.000   0.7589   0.01027   0.00331  -0.1120   0.3311   0.6931
   2.250   0.7860   0.01043   0.00345  -0.1117   0.3209   0.7104
   2.500   0.8129   0.01059   0.00358  -0.1114   0.3108   0.7279
   2.750   0.8400   0.01074   0.00372  -0.1112   0.3022   0.7430
   3.000   0.8668   0.01093   0.00386  -0.1109   0.2924   0.7543
   3.250   0.8936   0.01110   0.00401  -0.1106   0.2809   0.7658
   3.500   0.9198   0.01131   0.00417  -0.1102   0.2682   0.7769
   4.000   0.9711   0.01184   0.00455  -0.1094   0.2357   0.7985
   4.250   0.9961   0.01212   0.00477  -0.1089   0.2191   0.8128
   4.500   1.0202   0.01246   0.00503  -0.1082   0.1993   0.8291
   4.750   1.0428   0.01286   0.00534  -0.1073   0.1750   0.8502
   5.250   1.0791   0.01439   0.00651  -0.1042   0.0849   1.0000
   5.500   1.1039   0.01477   0.00685  -0.1037   0.0791   1.0000
   5.750   1.1288   0.01513   0.00717  -0.1033   0.0741   1.0000
   6.000   1.1533   0.01550   0.00751  -0.1028   0.0687   1.0000
   6.250   1.1755   0.01606   0.00795  -0.1020   0.0413   1.0000
   6.500   1.1971   0.01667   0.00849  -0.1011   0.0334   1.0000
   6.750   1.2204   0.01708   0.00892  -0.1004   0.0322   1.0000
   7.000   1.2432   0.01751   0.00936  -0.0997   0.0312   1.0000
   7.250   1.2655   0.01797   0.00983  -0.0989   0.0305   1.0000
   7.500   1.2871   0.01844   0.01033  -0.0980   0.0298   1.0000
   7.750   1.3086   0.01889   0.01081  -0.0970   0.0293   1.0000
   8.000   1.3294   0.01937   0.01132  -0.0960   0.0288   1.0000
   8.250   1.3493   0.01988   0.01187  -0.0949   0.0283   1.0000
   8.500   1.3672   0.02042   0.01245  -0.0934   0.0279   1.0000
   8.750   1.3838   0.02101   0.01308  -0.0918   0.0275   1.0000
   9.000   1.3992   0.02167   0.01378  -0.0901   0.0272   1.0000
   9.250   1.4132   0.02243   0.01459  -0.0882   0.0269   1.0000
   9.500   1.4248   0.02334   0.01556  -0.0862   0.0265   1.0000
   9.750   1.4386   0.02413   0.01639  -0.0845   0.0262   1.0000
  10.000   1.4515   0.02499   0.01731  -0.0828   0.0259   1.0000
  10.250   1.4633   0.02596   0.01834  -0.0811   0.0256   1.0000
  10.500   1.4737   0.02708   0.01951  -0.0795   0.0253   1.0000
  10.750   1.4830   0.02832   0.02082  -0.0779   0.0250   1.0000
  11.000   1.4910   0.02973   0.02229  -0.0763   0.0248   1.0000
  11.250   1.4980   0.03128   0.02392  -0.0749   0.0245   1.0000
  11.500   1.5036   0.03305   0.02576  -0.0736   0.0243   1.0000
  11.750   1.5078   0.03504   0.02783  -0.0725   0.0241   1.0000
  12.000   1.5101   0.03730   0.03018  -0.0715   0.0238   1.0000
  12.250   1.5103   0.03992   0.03288  -0.0707   0.0236   1.0000
  12.500   1.5076   0.04299   0.03604  -0.0702   0.0234   1.0000
  12.750   1.5018   0.04656   0.03971  -0.0699   0.0232   1.0000
  13.000   1.5012   0.04964   0.04290  -0.0698   0.0230   1.0000
  13.250   1.4997   0.05293   0.04629  -0.0699   0.0229   1.0000
  13.500   1.4966   0.05649   0.04995  -0.0701   0.0227   1.0000
  13.750   1.4922   0.06030   0.05387  -0.0705   0.0226   1.0000
  14.000   1.4864   0.06441   0.05809  -0.0710   0.0225   1.0000
  14.250   1.4797   0.06870   0.06248  -0.0717   0.0223   1.0000
  14.500   1.4726   0.07313   0.06702  -0.0725   0.0221   1.0000
  14.750   1.4650   0.07774   0.07173  -0.0734   0.0220   1.0000
  15.000   1.4573   0.08240   0.07649  -0.0744   0.0218   1.0000
  15.250   1.4497   0.08707   0.08126  -0.0754   0.0216   1.0000
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