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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 500,000
Max Cl/Cd: 95.24 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usnps4-il-500000.txt
Download as CSV file: xf-usnps4-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USNPS4 (smoothed)                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2144   0.09187   0.08965  -0.0591   0.9791   0.0201
  -7.750  -0.2055   0.08656   0.08435  -0.0671   0.9757   0.0212
  -7.500  -0.1966   0.07968   0.07745  -0.0783   0.9668   0.0214
  -7.250  -0.1796   0.07409   0.07185  -0.0839   0.9647   0.0217
  -7.000  -0.1580   0.07104   0.06879  -0.0866   0.9635   0.0220
  -6.750  -0.1475   0.06815   0.06589  -0.0878   0.9567   0.0223
  -6.500  -0.1232   0.06413   0.06183  -0.0932   0.9538   0.0229
  -6.250  -0.0937   0.05929   0.05691  -0.1002   0.9518   0.0241
  -5.750  -0.0451   0.04744   0.04471  -0.1110   0.9414   0.0266
  -5.500  -0.0149   0.04469   0.04190  -0.1142   0.9397   0.0272
  -5.250   0.0193   0.04122   0.03830  -0.1182   0.9385   0.0287
  -5.000   0.0738   0.01839   0.01522  -0.1201   0.9262   0.0320
  -4.750   0.1056   0.01630   0.01306  -0.1227   0.9247   0.0330
  -4.500   0.1377   0.01399   0.01056  -0.1248   0.9226   0.0354
  -4.250   0.1548   0.01127   0.00740  -0.1234   0.9144   0.0386
  -4.000   0.1873   0.00983   0.00590  -0.1254   0.9112   0.0398
  -3.750   0.2057   0.01802   0.01297  -0.1272   0.9175   0.0299
  -3.500   0.2389   0.01587   0.01043  -0.1280   0.9133   0.0303
  -3.250   0.2767   0.01461   0.00888  -0.1298   0.9102   0.0311
  -3.000   0.3027   0.01307   0.00718  -0.1293   0.9021   0.0319
  -2.750   0.3378   0.01229   0.00637  -0.1308   0.8964   0.0331
  -2.500   0.3667   0.01179   0.00582  -0.1309   0.8868   0.0346
  -2.250   0.4020   0.01133   0.00527  -0.1323   0.8789   0.0368
  -2.000   0.4313   0.01065   0.00452  -0.1325   0.8672   0.0386
  -1.750   0.4609   0.01029   0.00415  -0.1327   0.8541   0.0411
  -1.500   0.4908   0.01005   0.00384  -0.1330   0.8397   0.0442
  -1.250   0.5196   0.00972   0.00345  -0.1331   0.8235   0.0486
  -1.000   0.5481   0.00961   0.00326  -0.1331   0.8059   0.0535
  -0.750   0.5749   0.00942   0.00300  -0.1328   0.7866   0.0595
  -0.500   0.6012   0.00941   0.00290  -0.1323   0.7655   0.0662
  -0.250   0.6267   0.00934   0.00274  -0.1317   0.7439   0.0768
   0.000   0.6516   0.00931   0.00264  -0.1310   0.7212   0.0917
   0.250   0.6749   0.00884   0.00263  -0.1304   0.6983   0.3007
   0.500   0.7020   0.00742   0.00288  -0.1301   0.6750   1.0000
   0.750   0.7236   0.00762   0.00289  -0.1287   0.6508   1.0000
   1.000   0.7457   0.00783   0.00292  -0.1274   0.6269   1.0000
   1.250   0.7673   0.00806   0.00298  -0.1260   0.6026   1.0000
   1.500   0.7895   0.00829   0.00305  -0.1248   0.5784   1.0000
   1.750   0.8115   0.00854   0.00314  -0.1236   0.5554   1.0000
   2.000   0.8340   0.00879   0.00324  -0.1225   0.5329   1.0000
   2.250   0.8562   0.00905   0.00335  -0.1214   0.5104   1.0000
   2.500   0.8784   0.00932   0.00348  -0.1203   0.4895   1.0000
   2.750   0.9014   0.00957   0.00361  -0.1193   0.4700   1.0000
   3.000   0.9242   0.00983   0.00376  -0.1184   0.4512   1.0000
   3.250   0.9468   0.01010   0.00391  -0.1174   0.4330   1.0000
   3.500   0.9695   0.01037   0.00408  -0.1164   0.4162   1.0000
   3.750   0.9923   0.01063   0.00426  -0.1155   0.4009   1.0000
   4.000   1.0152   0.01090   0.00444  -0.1146   0.3868   1.0000
   4.250   1.0378   0.01117   0.00464  -0.1137   0.3732   1.0000
   4.500   1.0602   0.01145   0.00484  -0.1127   0.3602   1.0000
   4.750   1.0820   0.01175   0.00505  -0.1117   0.3482   1.0000
   5.000   1.1043   0.01200   0.00526  -0.1107   0.3371   1.0000
   5.250   1.1260   0.01227   0.00549  -0.1096   0.3272   1.0000
   5.500   1.1464   0.01260   0.00575  -0.1083   0.3175   1.0000
   5.750   1.1686   0.01285   0.00599  -0.1073   0.3081   1.0000
   6.000   1.1895   0.01317   0.00627  -0.1061   0.2994   1.0000
   6.250   1.2109   0.01347   0.00654  -0.1050   0.2910   1.0000
   6.500   1.2320   0.01379   0.00684  -0.1039   0.2836   1.0000
   6.750   1.2532   0.01410   0.00713  -0.1028   0.2762   1.0000
   7.000   1.2737   0.01446   0.00747  -0.1016   0.2696   1.0000
   7.250   1.2950   0.01476   0.00779  -0.1006   0.2629   1.0000
   7.500   1.3140   0.01520   0.00817  -0.0992   0.2563   1.0000
   7.750   1.3359   0.01547   0.00850  -0.0983   0.2504   1.0000
   8.000   1.3552   0.01588   0.00889  -0.0970   0.2446   1.0000
   8.250   1.3749   0.01628   0.00930  -0.0957   0.2395   1.0000
   8.500   1.3954   0.01663   0.00968  -0.0946   0.2345   1.0000
   8.750   1.4138   0.01709   0.01014  -0.0932   0.2296   1.0000
   9.000   1.4324   0.01755   0.01061  -0.0919   0.2251   1.0000
   9.250   1.4525   0.01792   0.01104  -0.0908   0.2205   1.0000
   9.500   1.4703   0.01840   0.01153  -0.0894   0.2160   1.0000
   9.750   1.4866   0.01900   0.01213  -0.0877   0.2117   1.0000
  10.000   1.5063   0.01939   0.01260  -0.0866   0.2083   1.0000
  10.250   1.5244   0.01987   0.01313  -0.0853   0.2045   1.0000
  10.500   1.5404   0.02048   0.01376  -0.0837   0.2009   1.0000
  10.750   1.5552   0.02118   0.01447  -0.0820   0.1973   1.0000
  11.000   1.5744   0.02157   0.01497  -0.0810   0.1932   1.0000
  11.250   1.5904   0.02214   0.01556  -0.0795   0.1879   1.0000
  11.500   1.6040   0.02290   0.01633  -0.0778   0.1829   1.0000
  11.750   1.6222   0.02337   0.01691  -0.0767   0.1788   1.0000
  12.000   1.6372   0.02405   0.01762  -0.0753   0.1747   1.0000
  12.250   1.6481   0.02499   0.01856  -0.0733   0.1703   1.0000
  12.500   1.6656   0.02552   0.01922  -0.0723   0.1663   1.0000
  12.750   1.6801   0.02626   0.02001  -0.0709   0.1616   1.0000
  13.000   1.6897   0.02733   0.02108  -0.0690   0.1568   1.0000
  13.250   1.7060   0.02798   0.02185  -0.0680   0.1520   1.0000
  13.500   1.7172   0.02899   0.02287  -0.0664   0.1460   1.0000
  13.750   1.7286   0.03000   0.02396  -0.0650   0.1407   1.0000
  14.000   1.7397   0.03107   0.02508  -0.0636   0.1345   1.0000
  14.250   1.7482   0.03236   0.02641  -0.0620   0.1283   1.0000
  14.500   1.7555   0.03379   0.02787  -0.0604   0.1201   1.0000
  14.750   1.7608   0.03543   0.02953  -0.0588   0.1097   1.0000
  15.000   1.7586   0.03779   0.03183  -0.0568   0.0952   1.0000
  15.250   1.7461   0.04122   0.03515  -0.0544   0.0732   1.0000
  15.500   1.7240   0.04581   0.03963  -0.0520   0.0522   1.0000
  15.750   1.7022   0.05074   0.04453  -0.0503   0.0390   1.0000
  16.000   1.6845   0.05557   0.04942  -0.0493   0.0316   1.0000
  16.250   1.6684   0.06046   0.05439  -0.0489   0.0275   1.0000
  16.500   1.6550   0.06524   0.05929  -0.0489   0.0248   1.0000
  16.750   1.6392   0.07055   0.06472  -0.0493   0.0230   1.0000
  17.000   1.6205   0.07648   0.07077  -0.0501   0.0216   1.0000
  17.250   1.6067   0.08181   0.07626  -0.0510   0.0207   1.0000
  17.500   1.5900   0.08774   0.08233  -0.0523   0.0199   1.0000
  17.750   1.5716   0.09406   0.08879  -0.0540   0.0193   1.0000
  18.000   1.5514   0.10075   0.09562  -0.0559   0.0189   1.0000
  18.250   1.5304   0.10767   0.10269  -0.0580   0.0185   1.0000
  18.500   1.5087   0.11487   0.11003  -0.0605   0.0182   1.0000
  18.750   1.4870   0.12220   0.11749  -0.0633   0.0179   1.0000
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