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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.14 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40-il-1000000.txt
Download as CSV file: xf-usa40-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7142   0.04752   0.04516  -0.0792   1.0000   0.0259
 -12.000  -0.7690   0.03979   0.03726  -0.0837   1.0000   0.0258
 -11.750  -0.7827   0.03435   0.03154  -0.0900   0.9981   0.0258
 -11.500  -0.7591   0.03031   0.02717  -0.0966   0.9950   0.0260
 -11.250  -0.7316   0.02766   0.02426  -0.1007   0.9928   0.0262
 -11.000  -0.7040   0.02579   0.02218  -0.1032   0.9894   0.0264
 -10.750  -0.6734   0.02434   0.02056  -0.1057   0.9869   0.0266
 -10.500  -0.6409   0.02326   0.01932  -0.1079   0.9851   0.0267
 -10.250  -0.6123   0.02016   0.01594  -0.1110   0.9834   0.0271
 -10.000  -0.5806   0.01883   0.01452  -0.1129   0.9814   0.0274
  -9.750  -0.5517   0.01794   0.01359  -0.1138   0.9767   0.0277
  -9.500  -0.5198   0.01723   0.01284  -0.1151   0.9734   0.0280
  -9.250  -0.4874   0.01659   0.01214  -0.1164   0.9705   0.0284
  -9.000  -0.4597   0.01597   0.01146  -0.1166   0.9637   0.0287
  -8.750  -0.4299   0.01528   0.01070  -0.1173   0.9576   0.0290
  -8.500  -0.4024   0.01466   0.01000  -0.1173   0.9482   0.0293
  -8.250  -0.3742   0.01406   0.00932  -0.1175   0.9376   0.0295
  -8.000  -0.3469   0.01354   0.00870  -0.1174   0.9251   0.0298
  -7.750  -0.3200   0.01306   0.00814  -0.1172   0.9123   0.0301
  -7.500  -0.2926   0.01264   0.00763  -0.1170   0.9008   0.0304
  -7.250  -0.2651   0.01229   0.00718  -0.1169   0.8891   0.0306
  -7.000  -0.2376   0.01199   0.00680  -0.1167   0.8767   0.0308
  -6.750  -0.2110   0.01122   0.00595  -0.1166   0.8648   0.0314
  -6.500  -0.1837   0.01078   0.00544  -0.1165   0.8525   0.0319
  -6.250  -0.1560   0.01048   0.00508  -0.1164   0.8393   0.0324
  -6.000  -0.1281   0.01024   0.00480  -0.1163   0.8262   0.0330
  -5.750  -0.1002   0.01003   0.00452  -0.1162   0.8128   0.0337
  -5.500  -0.0723   0.00982   0.00423  -0.1160   0.7982   0.0342
  -5.250  -0.0444   0.00963   0.00395  -0.1159   0.7829   0.0348
  -5.000  -0.0163   0.00947   0.00371  -0.1157   0.7674   0.0353
  -4.750   0.0116   0.00922   0.00339  -0.1156   0.7507   0.0360
  -4.500   0.0395   0.00900   0.00309  -0.1155   0.7332   0.0371
  -4.250   0.0676   0.00888   0.00290  -0.1154   0.7160   0.0382
  -4.000   0.0957   0.00878   0.00273  -0.1153   0.6996   0.0394
  -3.750   0.1239   0.00871   0.00258  -0.1152   0.6833   0.0405
  -3.500   0.1521   0.00857   0.00238  -0.1151   0.6679   0.0430
  -3.250   0.1804   0.00850   0.00227  -0.1150   0.6543   0.0458
  -2.750   0.2373   0.00831   0.00205  -0.1149   0.6284   0.0599
  -2.500   0.2658   0.00824   0.00197  -0.1149   0.6161   0.0708
  -2.250   0.2941   0.00820   0.00191  -0.1148   0.6037   0.0796
  -2.000   0.3228   0.00812   0.00183  -0.1149   0.5917   0.0900
  -1.750   0.3513   0.00802   0.00176  -0.1149   0.5787   0.1090
  -1.500   0.3795   0.00785   0.00173  -0.1150   0.5627   0.1648
  -1.250   0.4077   0.00783   0.00172  -0.1149   0.5450   0.1952
  -1.000   0.4358   0.00785   0.00171  -0.1149   0.5250   0.2140
  -0.750   0.4637   0.00789   0.00171  -0.1148   0.5044   0.2325
  -0.500   0.4915   0.00792   0.00172  -0.1147   0.4830   0.2600
  -0.250   0.5192   0.00786   0.00176  -0.1147   0.4628   0.3239
   0.000   0.5471   0.00779   0.00182  -0.1148   0.4457   0.4006
   0.250   0.5752   0.00772   0.00187  -0.1148   0.4316   0.4707
   0.500   0.6032   0.00765   0.00196  -0.1148   0.4191   0.5479
   0.750   0.6311   0.00767   0.00206  -0.1147   0.4071   0.6029
   1.000   0.6587   0.00776   0.00216  -0.1146   0.3940   0.6425
   1.250   0.6867   0.00783   0.00225  -0.1144   0.3834   0.6724
   1.500   0.7145   0.00795   0.00236  -0.1143   0.3721   0.6951
   1.750   0.7421   0.00809   0.00246  -0.1141   0.3601   0.7118
   2.000   0.7701   0.00819   0.00255  -0.1139   0.3513   0.7293
   2.250   0.7976   0.00834   0.00266  -0.1137   0.3413   0.7421
   2.750   0.8530   0.00859   0.00287  -0.1134   0.3236   0.7644
   3.000   0.8807   0.00871   0.00297  -0.1133   0.3150   0.7753
   3.250   0.9079   0.00888   0.00309  -0.1131   0.3048   0.7859
   3.500   0.9346   0.00907   0.00323  -0.1128   0.2903   0.7949
   4.000   0.9882   0.00943   0.00350  -0.1123   0.2647   0.8147
   4.250   1.0146   0.00965   0.00366  -0.1119   0.2505   0.8245
   4.500   1.0402   0.00991   0.00385  -0.1115   0.2330   0.8367
   4.750   1.0646   0.01023   0.00409  -0.1109   0.2113   0.8536
   5.000   1.0865   0.01062   0.00440  -0.1098   0.1817   0.8847
   5.250   1.1013   0.01174   0.00517  -0.1078   0.1022   1.0000
   5.500   1.1241   0.01237   0.00565  -0.1071   0.0804   1.0000
   5.750   1.1496   0.01271   0.00593  -0.1067   0.0728   1.0000
   6.000   1.1745   0.01308   0.00624  -0.1062   0.0639   1.0000
   6.250   1.1956   0.01382   0.00681  -0.1052   0.0345   1.0000
   6.500   1.2206   0.01414   0.00713  -0.1048   0.0325   1.0000
   6.750   1.2453   0.01448   0.00747  -0.1043   0.0316   1.0000
   7.000   1.2696   0.01484   0.00785  -0.1037   0.0308   1.0000
   7.250   1.2931   0.01524   0.00826  -0.1030   0.0299   1.0000
   7.500   1.3159   0.01569   0.00873  -0.1022   0.0290   1.0000
   7.750   1.3387   0.01611   0.00917  -0.1014   0.0286   1.0000
   8.000   1.3614   0.01651   0.00959  -0.1007   0.0283   1.0000
   8.250   1.3833   0.01696   0.01005  -0.0998   0.0279   1.0000
   8.500   1.4045   0.01743   0.01055  -0.0988   0.0275   1.0000
   8.750   1.4247   0.01794   0.01109  -0.0977   0.0271   1.0000
   9.000   1.4439   0.01849   0.01167  -0.0964   0.0266   1.0000
   9.250   1.4606   0.01910   0.01232  -0.0947   0.0261   1.0000
   9.500   1.4744   0.01981   0.01306  -0.0926   0.0257   1.0000
   9.750   1.4854   0.02067   0.01398  -0.0902   0.0253   1.0000
  10.000   1.4916   0.02183   0.01522  -0.0873   0.0249   1.0000
  10.250   1.5057   0.02253   0.01596  -0.0856   0.0248   1.0000
  10.500   1.5187   0.02333   0.01681  -0.0838   0.0246   1.0000
  10.750   1.5303   0.02426   0.01778  -0.0820   0.0244   1.0000
  11.000   1.5410   0.02528   0.01886  -0.0802   0.0241   1.0000
  11.250   1.5508   0.02643   0.02006  -0.0786   0.0238   1.0000
  11.500   1.5591   0.02774   0.02143  -0.0769   0.0234   1.0000
  11.750   1.5662   0.02923   0.02299  -0.0754   0.0232   1.0000
  12.000   1.5717   0.03093   0.02474  -0.0740   0.0229   1.0000
  12.250   1.5760   0.03284   0.02673  -0.0727   0.0227   1.0000
  12.500   1.5786   0.03502   0.02898  -0.0716   0.0224   1.0000
  12.750   1.5792   0.03751   0.03155  -0.0707   0.0222   1.0000
  13.000   1.5776   0.04038   0.03450  -0.0700   0.0221   1.0000
  13.250   1.5726   0.04376   0.03796  -0.0696   0.0219   1.0000
  13.500   1.5641   0.04769   0.04199  -0.0694   0.0217   1.0000
  13.750   1.5513   0.05228   0.04668  -0.0695   0.0215   1.0000
  14.000   1.5330   0.05763   0.05214  -0.0697   0.0214   1.0000
  14.250   1.5316   0.06108   0.05568  -0.0701   0.0212   1.0000
  14.500   1.5320   0.06436   0.05904  -0.0705   0.0211   1.0000
  14.750   1.5296   0.06805   0.06281  -0.0710   0.0209   1.0000
  15.000   1.5253   0.07204   0.06689  -0.0716   0.0208   1.0000
  15.250   1.5199   0.07624   0.07118  -0.0723   0.0207   1.0000
  15.500   1.5142   0.08050   0.07552  -0.0731   0.0205   1.0000
  15.750   1.5081   0.08484   0.07994  -0.0740   0.0204   1.0000
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