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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 500,000
Max Cl/Cd: 119.5 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-500000-n5.txt
Download as CSV file: xf-fx74130wp2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1699   0.08809   0.08444  -0.0959   0.7486   0.0091
  -9.750  -0.1661   0.08486   0.08123  -0.0975   0.7477   0.0101
  -9.500  -0.1641   0.08125   0.07765  -0.0993   0.7468   0.0105
  -9.250  -0.1636   0.07753   0.07396  -0.1011   0.7459   0.0097
  -9.000  -0.1594   0.07303   0.06949  -0.1051   0.7448   0.0118
  -8.750  -0.1599   0.06869   0.06518  -0.1083   0.7437   0.0119
  -8.500  -0.1657   0.06378   0.06029  -0.1123   0.7425   0.0119
  -8.250  -0.1746   0.05972   0.05620  -0.1140   0.7412   0.0119
  -7.750  -0.1856   0.05306   0.04938  -0.1137   0.7388   0.0119
  -6.750  -0.1878   0.03505   0.03060  -0.1095   0.7350   0.0075
  -6.500  -0.1790   0.03146   0.02675  -0.1083   0.7341   0.0073
  -6.250  -0.1657   0.02820   0.02320  -0.1071   0.7332   0.0071
  -6.000  -0.1498   0.02495   0.01958  -0.1058   0.7321   0.0069
  -5.750  -0.1309   0.02216   0.01642  -0.1047   0.7311   0.0068
  -5.500  -0.1097   0.01959   0.01347  -0.1037   0.7300   0.0067
  -5.250  -0.0861   0.01777   0.01133  -0.1031   0.7290   0.0068
  -5.000  -0.0612   0.01637   0.00969  -0.1026   0.7281   0.0069
  -4.750  -0.0358   0.01531   0.00844  -0.1023   0.7273   0.0071
  -4.500  -0.0100   0.01453   0.00752  -0.1021   0.7265   0.0075
  -4.250   0.0161   0.01394   0.00683  -0.1019   0.7257   0.0077
  -4.000   0.0404   0.01302   0.00582  -0.1015   0.7250   0.0083
  -3.750   0.0663   0.01256   0.00531  -0.1015   0.7242   0.0087
  -3.500   0.0929   0.01225   0.00497  -0.1015   0.7235   0.0095
  -3.250   0.1198   0.01201   0.00469  -0.1017   0.7227   0.0106
  -3.000   0.1464   0.01168   0.00431  -0.1017   0.7218   0.0111
  -2.750   0.1731   0.01139   0.00398  -0.1017   0.7208   0.0116
  -2.500   0.2002   0.01114   0.00368  -0.1018   0.7199   0.0126
  -2.250   0.2274   0.01092   0.00345  -0.1019   0.7190   0.0162
  -2.000   0.2546   0.01069   0.00328  -0.1021   0.7180   0.0384
  -1.750   0.2812   0.01034   0.00318  -0.1023   0.7170   0.1102
  -1.500   0.3028   0.00876   0.00299  -0.1027   0.7159   0.5253
  -1.250   0.3252   0.00826   0.00326  -0.1017   0.7148   0.7516
  -1.000   0.3529   0.00843   0.00339  -0.1017   0.7138   0.7913
  -0.750   0.3790   0.00861   0.00359  -0.1012   0.7130   0.8118
  -0.500   0.4061   0.00873   0.00369  -0.1010   0.7122   0.8231
  -0.250   0.4338   0.00883   0.00375  -0.1011   0.7114   0.8307
   0.000   0.4616   0.00889   0.00377  -0.1012   0.7105   0.8356
   0.250   0.4896   0.00893   0.00380  -0.1013   0.7097   0.8389
   0.500   0.5183   0.00899   0.00381  -0.1017   0.7089   0.8414
   0.750   0.5466   0.00904   0.00387  -0.1021   0.7079   0.8435
   1.000   0.5750   0.00910   0.00393  -0.1026   0.7068   0.8454
   1.250   0.6035   0.00915   0.00399  -0.1031   0.7054   0.8470
   1.500   0.6315   0.00919   0.00404  -0.1034   0.7041   0.8481
   1.750   0.6595   0.00924   0.00411  -0.1037   0.7028   0.8491
   2.000   0.6877   0.00927   0.00417  -0.1041   0.7015   0.8502
   2.250   0.7162   0.00928   0.00419  -0.1045   0.6998   0.8511
   2.500   0.7449   0.00926   0.00418  -0.1049   0.6980   0.8521
   2.750   0.7739   0.00925   0.00418  -0.1054   0.6964   0.8532
   3.000   0.8026   0.00926   0.00421  -0.1058   0.6948   0.8543
   3.250   0.8295   0.00929   0.00431  -0.1060   0.6916   0.8554
   3.500   0.8572   0.00926   0.00433  -0.1062   0.6881   0.8564
   3.750   0.8859   0.00918   0.00430  -0.1066   0.6846   0.8574
   4.000   0.9146   0.00910   0.00424  -0.1070   0.6810   0.8585
   4.250   0.9410   0.00907   0.00430  -0.1070   0.6746   0.8598
   4.500   0.9693   0.00893   0.00416  -0.1072   0.6679   0.8608
   4.750   0.9953   0.00886   0.00418  -0.1071   0.6568   0.8617
   5.000   1.0212   0.00878   0.00414  -0.1068   0.6424   0.8626
   5.250   1.0456   0.00875   0.00411  -0.1063   0.6171   0.8636
   5.500   1.0573   0.00921   0.00418  -0.1033   0.5382   0.8651
   5.750   1.0548   0.01044   0.00493  -0.0981   0.4505   0.8673
   6.000   1.0539   0.01152   0.00570  -0.0933   0.3850   0.8701
   6.250   1.0528   0.01238   0.00638  -0.0885   0.3390   0.8727
   6.500   1.0498   0.01333   0.00715  -0.0835   0.2976   0.8753
   6.750   1.0464   0.01443   0.00810  -0.0789   0.2573   0.8780
   7.000   1.0448   0.01568   0.00917  -0.0750   0.2165   0.8810
   7.250   1.0451   0.01700   0.01031  -0.0717   0.1747   0.8840
   7.500   1.0489   0.01825   0.01139  -0.0690   0.1382   0.8870
   7.750   1.0553   0.01940   0.01240  -0.0667   0.1079   0.8899
   8.000   1.0628   0.02047   0.01339  -0.0646   0.0827   0.8932
   8.250   1.0705   0.02160   0.01441  -0.0625   0.0584   0.8967
   8.500   1.0805   0.02263   0.01539  -0.0608   0.0429   0.9003
   8.750   1.0918   0.02359   0.01632  -0.0593   0.0317   0.9041
   9.000   1.1027   0.02454   0.01726  -0.0577   0.0230   0.9089
   9.250   1.1161   0.02536   0.01812  -0.0564   0.0192   0.9146
   9.500   1.1277   0.02626   0.01905  -0.0549   0.0154   0.9227
   9.750   1.1424   0.02706   0.01995  -0.0538   0.0130   0.9362
  10.000   1.1577   0.02808   0.02101  -0.0534   0.0098   0.9925
  10.500   1.1819   0.03028   0.02330  -0.0512   0.0062   1.0000
  10.750   1.1944   0.03140   0.02449  -0.0501   0.0057   1.0000
  11.000   1.2063   0.03259   0.02576  -0.0491   0.0050   1.0000
  11.250   1.2178   0.03384   0.02708  -0.0480   0.0045   1.0000
  11.500   1.2284   0.03517   0.02848  -0.0470   0.0043   1.0000
  11.750   1.2378   0.03666   0.03004  -0.0459   0.0040   1.0000
  12.000   1.2453   0.03834   0.03182  -0.0447   0.0038   1.0000
  12.250   1.2517   0.04017   0.03376  -0.0434   0.0037   1.0000
  12.500   1.2621   0.04164   0.03532  -0.0426   0.0035   1.0000
  12.750   1.2709   0.04330   0.03708  -0.0417   0.0034   1.0000
  13.000   1.2797   0.04499   0.03890  -0.0409   0.0032   1.0000
  13.250   1.2878   0.04680   0.04081  -0.0401   0.0031   1.0000
  13.500   1.2943   0.04878   0.04292  -0.0393   0.0030   1.0000
  13.750   1.3006   0.05085   0.04510  -0.0385   0.0029   1.0000
  14.000   1.3055   0.05313   0.04750  -0.0378   0.0028   1.0000
  14.250   1.3106   0.05543   0.04993  -0.0372   0.0027   1.0000
  14.500   1.3150   0.05787   0.05249  -0.0367   0.0027   1.0000
  14.750   1.3177   0.06055   0.05531  -0.0362   0.0026   1.0000
  15.000   1.3197   0.06340   0.05831  -0.0359   0.0026   1.0000
  15.250   1.3216   0.06633   0.06138  -0.0357   0.0025   1.0000
  15.500   1.3215   0.06961   0.06480  -0.0356   0.0025   1.0000
  15.750   1.3209   0.07302   0.06837  -0.0358   0.0024   1.0000
  16.000   1.3192   0.07668   0.07218  -0.0361   0.0024   1.0000
  16.250   1.3160   0.08068   0.07633  -0.0367   0.0023   1.0000
  16.500   1.3108   0.08513   0.08097  -0.0375   0.0023   1.0000
  16.750   1.3050   0.08979   0.08579  -0.0386   0.0023   1.0000
  17.000   1.2969   0.09497   0.09114  -0.0402   0.0022   1.0000
  17.250   1.2878   0.10054   0.09689  -0.0420   0.0022   1.0000
  17.500   1.2773   0.10654   0.10307  -0.0444   0.0022   1.0000
  17.750   1.2659   0.11294   0.10965  -0.0472   0.0022   1.0000
  18.000   1.2521   0.12004   0.11694  -0.0506   0.0022   1.0000
  18.250   1.2386   0.12734   0.12442  -0.0545   0.0021   1.0000
  18.500   1.2244   0.13512   0.13237  -0.0589   0.0021   1.0000
  18.750   1.2103   0.14319   0.14061  -0.0636   0.0022   1.0000
  19.000   1.1957   0.15174   0.14932  -0.0689   0.0022   1.0000
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