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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 500,000
Max Cl/Cd: 125.81 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-500000.txt
Download as CSV file: xf-fx74130wp2-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1104   0.08725   0.08411  -0.0884   0.7824   0.0146
 -10.250  -0.1080   0.08359   0.08044  -0.0898   0.7816   0.0151
 -10.000  -0.1059   0.07986   0.07672  -0.0913   0.7809   0.0155
  -9.750  -0.1053   0.07588   0.07275  -0.0929   0.7801   0.0164
  -9.500  -0.1051   0.07186   0.06874  -0.0949   0.7794   0.0171
  -9.250  -0.1051   0.06790   0.06478  -0.0967   0.7786   0.0173
  -9.000  -0.1039   0.06416   0.06105  -0.0996   0.7777   0.0180
  -8.750  -0.1050   0.06000   0.05691  -0.1022   0.7769   0.0181
  -8.500  -0.1087   0.05529   0.05223  -0.1055   0.7761   0.0181
  -8.250  -0.1177   0.05033   0.04726  -0.1096   0.7750   0.0181
  -8.000  -0.1284   0.04665   0.04355  -0.1110   0.7736   0.0181
  -7.750  -0.1416   0.04378   0.04064  -0.1102   0.7720   0.0181
  -7.500  -0.1690   0.05353   0.05005  -0.1162   0.7733   0.0181
  -7.250  -0.1657   0.05060   0.04698  -0.1156   0.7718   0.0182
  -7.000  -0.1605   0.04772   0.04394  -0.1148   0.7704   0.0182
  -6.750  -0.1531   0.04491   0.04094  -0.1139   0.7692   0.0182
  -6.500  -0.1623   0.03779   0.03357  -0.1127   0.7680   0.0192
  -6.250  -0.1479   0.03558   0.03126  -0.1123   0.7670   0.0198
  -6.000  -0.1316   0.03375   0.02932  -0.1119   0.7661   0.0205
  -5.750  -0.1139   0.03179   0.02719  -0.1113   0.7652   0.0213
  -5.500  -0.0947   0.02991   0.02510  -0.1106   0.7643   0.0227
  -5.250  -0.0733   0.02824   0.02318  -0.1099   0.7633   0.0247
  -5.000  -0.0449   0.02900   0.02371  -0.1091   0.7622   0.0271
  -4.750  -0.0313   0.02408   0.01837  -0.1081   0.7610   0.0289
  -4.500  -0.0080   0.02243   0.01665  -0.1080   0.7599   0.0305
  -4.250   0.0200   0.01934   0.01299  -0.1061   0.7589   0.0189
  -4.000   0.0454   0.01712   0.01062  -0.1055   0.7578   0.0160
  -3.750   0.0713   0.01592   0.00929  -0.1050   0.7568   0.0160
  -3.500   0.0969   0.01509   0.00838  -0.1046   0.7557   0.0164
  -3.250   0.1226   0.01447   0.00770  -0.1043   0.7546   0.0171
  -3.000   0.1497   0.01430   0.00748  -0.1043   0.7536   0.0183
  -2.750   0.1739   0.01347   0.00658  -0.1039   0.7526   0.0191
  -2.500   0.1997   0.01298   0.00602  -0.1037   0.7518   0.0204
  -2.250   0.2265   0.01273   0.00572  -0.1037   0.7510   0.0237
  -2.000   0.2499   0.01174   0.00540  -0.1036   0.7501   0.2241
  -1.750   0.2691   0.01017   0.00534  -0.1035   0.7490   0.6584
  -1.500   0.2904   0.01049   0.00602  -0.1016   0.7475   0.8026
  -1.250   0.3134   0.01084   0.00640  -0.1002   0.7460   0.8256
  -1.000   0.3364   0.01114   0.00670  -0.0989   0.7447   0.8411
  -0.750   0.3568   0.01146   0.00703  -0.0969   0.7435   0.8589
  -0.500   0.3773   0.01166   0.00724  -0.0950   0.7422   0.8709
  -0.250   0.4007   0.01175   0.00732  -0.0939   0.7410   0.8787
   0.000   0.4253   0.01185   0.00738  -0.0932   0.7398   0.8850
   0.250   0.4524   0.01193   0.00742  -0.0933   0.7389   0.8898
   0.500   0.4780   0.01196   0.00744  -0.0930   0.7379   0.8927
   0.750   0.5053   0.01204   0.00748  -0.0931   0.7370   0.8953
   1.000   0.5329   0.01218   0.00760  -0.0934   0.7359   0.8978
   1.250   0.5583   0.01231   0.00777  -0.0935   0.7336   0.9001
   1.500   0.5859   0.01241   0.00788  -0.0939   0.7312   0.9020
   1.750   0.6135   0.01242   0.00789  -0.0942   0.7292   0.9035
   2.000   0.6412   0.01240   0.00789  -0.0945   0.7276   0.9049
   2.250   0.6693   0.01239   0.00788  -0.0948   0.7262   0.9063
   2.500   0.6981   0.01239   0.00788  -0.0953   0.7249   0.9076
   2.750   0.7282   0.01235   0.00784  -0.0960   0.7236   0.9087
   3.000   0.7577   0.01237   0.00787  -0.0966   0.7221   0.9101
   3.250   0.7816   0.01248   0.00806  -0.0964   0.7181   0.9117
   3.500   0.8106   0.01241   0.00803  -0.0969   0.7153   0.9128
   3.750   0.8415   0.01220   0.00783  -0.0977   0.7128   0.9138
   4.000   0.8738   0.01195   0.00760  -0.0987   0.7106   0.9149
   4.250   0.9056   0.01173   0.00738  -0.0996   0.7079   0.9159
   4.500   0.9313   0.01154   0.00728  -0.0995   0.7021   0.9170
   4.750   0.9636   0.01100   0.00675  -0.1002   0.6976   0.9178
   5.000   0.9921   0.01060   0.00641  -0.1003   0.6913   0.9189
   5.250   1.0210   0.01018   0.00603  -0.1005   0.6846   0.9200
   5.500   1.0473   0.00975   0.00567  -0.1002   0.6745   0.9217
   5.750   1.0736   0.00943   0.00541  -0.0999   0.6632   0.9234
   6.000   1.0999   0.00927   0.00534  -0.0998   0.6525   0.9249
   6.250   1.1247   0.00916   0.00531  -0.0994   0.6346   0.9266
   6.500   1.1461   0.00911   0.00518  -0.0982   0.5942   0.9285
   6.750   1.1486   0.00981   0.00545  -0.0936   0.5120   0.9317
   7.000   1.1390   0.01091   0.00619  -0.0870   0.4420   0.9371
   7.250   1.1238   0.01197   0.00701  -0.0796   0.3869   0.9448
   7.500   1.1075   0.01326   0.00809  -0.0727   0.3371   0.9572
   7.750   1.1011   0.01515   0.00968  -0.0693   0.2724   1.0000
   8.000   1.0968   0.01714   0.01133  -0.0663   0.2103   1.0000
   8.250   1.0939   0.01910   0.01294  -0.0635   0.1480   1.0000
   8.500   1.0948   0.02085   0.01438  -0.0611   0.0973   1.0000
   8.750   1.0992   0.02242   0.01570  -0.0591   0.0607   1.0000
   9.000   1.1080   0.02373   0.01689  -0.0576   0.0417   1.0000
   9.250   1.1192   0.02488   0.01800  -0.0563   0.0321   1.0000
   9.500   1.1322   0.02592   0.01905  -0.0552   0.0261   1.0000
   9.750   1.1439   0.02707   0.02023  -0.0540   0.0205   1.0000
  10.000   1.1497   0.02869   0.02187  -0.0520   0.0147   1.0000
  10.250   1.1617   0.02987   0.02309  -0.0509   0.0120   1.0000
  10.500   1.1631   0.03189   0.02519  -0.0487   0.0100   1.0000
  10.750   1.1702   0.03352   0.02694  -0.0471   0.0095   1.0000
  11.000   1.1795   0.03501   0.02852  -0.0458   0.0089   1.0000
  11.250   1.1878   0.03661   0.03022  -0.0444   0.0085   1.0000
  11.500   1.1963   0.03826   0.03197  -0.0431   0.0082   1.0000
  11.750   1.2061   0.03983   0.03362  -0.0420   0.0078   1.0000
  12.000   1.2163   0.04136   0.03523  -0.0410   0.0074   1.0000
  12.250   1.2260   0.04299   0.03693  -0.0401   0.0070   1.0000
  12.500   1.2341   0.04484   0.03885  -0.0391   0.0066   1.0000
  12.750   1.2418   0.04703   0.04117  -0.0378   0.0064   1.0000
  13.000   1.2517   0.04946   0.04379  -0.0365   0.0063   1.0000
  13.250   1.2616   0.05242   0.04700  -0.0352   0.0061   1.0000
  13.500   1.2676   0.05492   0.04972  -0.0343   0.0061   1.0000
  13.750   1.2708   0.05753   0.05253  -0.0335   0.0060   1.0000
  14.000   1.2711   0.06079   0.05602  -0.0326   0.0060   1.0000
  14.250   1.2684   0.06432   0.05978  -0.0318   0.0059   1.0000
  14.500   1.2623   0.06836   0.06405  -0.0312   0.0059   1.0000
  14.750   1.2524   0.07302   0.06896  -0.0308   0.0059   1.0000
  15.000   1.2391   0.07828   0.07446  -0.0309   0.0059   1.0000
  15.250   1.2242   0.08384   0.08026  -0.0314   0.0059   1.0000
  15.500   1.2063   0.09019   0.08683  -0.0326   0.0060   1.0000
  15.750   1.1867   0.09713   0.09399  -0.0344   0.0060   1.0000
  16.000   1.1665   0.10456   0.10163  -0.0371   0.0060   1.0000
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