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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 200,000
Max Cl/Cd: 72.55 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-200000.txt
Download as CSV file: xf-fx74130wp2-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1439   0.09623   0.09217  -0.1044   0.8622   0.0367
 -10.000  -0.1435   0.09330   0.08925  -0.1071   0.8605   0.0377
  -9.750  -0.1457   0.09028   0.08629  -0.1105   0.8584   0.0383
  -9.500  -0.1056   0.07508   0.07143  -0.1073   0.8514   0.0395
  -9.250  -0.0920   0.07184   0.06817  -0.1054   0.8504   0.0410
  -9.000  -0.0861   0.06881   0.06514  -0.1056   0.8492   0.0422
  -8.750  -0.0846   0.06549   0.06182  -0.1066   0.8479   0.0432
  -8.500  -0.0854   0.06206   0.05840  -0.1079   0.8465   0.0444
  -8.250  -0.1701   0.06768   0.06380  -0.1226   0.8472   0.0402
  -8.000  -0.1638   0.06525   0.06137  -0.1220   0.8457   0.0411
  -7.750  -0.1618   0.06286   0.05898  -0.1220   0.8437   0.0422
  -7.500  -0.1615   0.06028   0.05637  -0.1222   0.8418   0.0431
  -7.250  -0.1599   0.05772   0.05374  -0.1223   0.8400   0.0445
  -7.000  -0.1569   0.05512   0.05103  -0.1223   0.8383   0.0462
  -6.750  -0.1521   0.05255   0.04827  -0.1221   0.8366   0.0488
  -6.250  -0.1419   0.04675   0.04190  -0.1204   0.8331   0.0537
  -6.000  -0.1285   0.04468   0.03984  -0.1199   0.8318   0.0558
  -5.750  -0.1164   0.04306   0.03812  -0.1192   0.8300   0.0590
  -5.500  -0.1084   0.04167   0.03621  -0.1173   0.8279   0.0667
  -5.250  -0.0939   0.03942   0.03404  -0.1168   0.8259   0.0693
  -4.750  -0.0632   0.03638   0.03063  -0.1148   0.8224   0.0838
  -4.500  -0.0460   0.03502   0.02905  -0.1140   0.8211   0.0968
  -4.250  -0.0105   0.03102   0.02385  -0.1104   0.8201   0.0394
  -4.000   0.0137   0.02805   0.02069  -0.1098   0.8191   0.0347
  -3.750   0.0217   0.02801   0.02052  -0.1071   0.8159   0.0360
  -3.500   0.0303   0.02790   0.02028  -0.1044   0.8134   0.0364
  -3.250   0.0449   0.02736   0.01959  -0.1024   0.8112   0.0363
  -3.000   0.0669   0.02649   0.01861  -0.1013   0.8093   0.0357
  -2.750   0.0894   0.02583   0.01788  -0.1003   0.8079   0.0358
  -2.500   0.1133   0.02531   0.01730  -0.0997   0.8068   0.0370
  -2.250   0.1405   0.02482   0.01677  -0.0996   0.8058   0.0391
  -2.000   0.1696   0.02410   0.01601  -0.0999   0.8049   0.0527
  -1.750   0.1169   0.02647   0.01842  -0.0883   0.7969   0.0437
  -1.500   0.1395   0.02524   0.01801  -0.0883   0.7952   0.2388
  -1.250   0.1366   0.02433   0.01916  -0.0809   0.7933   0.8316
  -1.000   0.1409   0.02476   0.01963  -0.0735   0.7917   0.8847
  -0.500   0.3128   0.02528   0.01978  -0.0909   0.7925   0.9784
  -0.250   0.3598   0.02524   0.01960  -0.0948   0.7917   0.9824
   0.000   0.3499   0.02690   0.02129  -0.0915   0.7840   0.9929
   0.250   0.3870   0.02708   0.02139  -0.0940   0.7818   0.9957
   0.500   0.4291   0.02712   0.02134  -0.0972   0.7803   0.9973
   0.750   0.4711   0.02711   0.02126  -0.1002   0.7791   0.9987
   1.000   0.5120   0.02705   0.02114  -0.1029   0.7781   0.9998
   1.250   0.4293   0.02878   0.02293  -0.0851   0.7661   1.0000
   1.500   0.3915   0.02961   0.02377  -0.0747   0.7573   1.0000
   1.750   0.4077   0.02973   0.02385  -0.0730   0.7535   1.0000
   2.000   0.4412   0.02973   0.02381  -0.0740   0.7515   1.0000
   2.250   0.4828   0.02968   0.02373  -0.0763   0.7504   1.0000
   2.500   0.4453   0.03034   0.02439  -0.0663   0.7388   1.0000
   2.750   0.4822   0.03034   0.02437  -0.0678   0.7373   1.0000
   3.000   0.5210   0.03034   0.02437  -0.0696   0.7359   1.0000
   3.250   0.5141   0.03116   0.02519  -0.0656   0.7250   1.0000
   3.500   0.5533   0.03106   0.02510  -0.0673   0.7235   1.0000
   3.750   0.5941   0.03092   0.02499  -0.0693   0.7225   1.0000
   4.000   0.5947   0.03176   0.02584  -0.0665   0.7111   1.0000
   4.250   0.6343   0.03156   0.02570  -0.0683   0.7097   1.0000
   4.500   0.6768   0.03119   0.02538  -0.0703   0.7088   1.0000
   4.750   0.6812   0.03199   0.02621  -0.0680   0.6974   1.0000
   5.000   0.6981   0.03247   0.02674  -0.0672   0.6893   1.0000
   5.250   0.7326   0.03219   0.02656  -0.0682   0.6855   1.0000
   5.500   0.7738   0.03157   0.02602  -0.0698   0.6838   1.0000
   5.750   0.7915   0.03186   0.02639  -0.0688   0.6747   1.0000
   6.000   0.8335   0.03091   0.02555  -0.0703   0.6719   1.0000
   6.250   0.8827   0.02938   0.02418  -0.0723   0.6704   1.0000
   6.500   0.9443   0.02669   0.02168  -0.0753   0.6697   1.0000
   6.750   1.0047   0.02358   0.01877  -0.0777   0.6662   1.0000
   7.000   1.0571   0.02058   0.01594  -0.0793   0.6575   1.0000
   7.250   1.0866   0.01892   0.01441  -0.0782   0.6437   1.0000
   7.500   1.0933   0.01902   0.01461  -0.0751   0.6258   1.0000
   7.750   1.1084   0.01893   0.01463  -0.0733   0.6016   1.0000
   8.000   1.1601   0.01599   0.01101  -0.0732   0.4761   1.0000
   8.250   1.1442   0.01791   0.01239  -0.0675   0.3973   1.0000
   8.500   1.1270   0.02028   0.01431  -0.0626   0.3281   1.0000
   8.750   1.1105   0.02288   0.01645  -0.0581   0.2565   1.0000
   9.000   1.0952   0.02562   0.01866  -0.0541   0.1787   1.0000
   9.250   1.0839   0.02831   0.02082  -0.0507   0.1101   1.0000
   9.500   1.0797   0.03066   0.02286  -0.0479   0.0748   1.0000
   9.750   1.0822   0.03260   0.02471  -0.0458   0.0591   1.0000
  10.000   1.0874   0.03437   0.02648  -0.0441   0.0483   1.0000
  10.250   1.0915   0.03631   0.02843  -0.0423   0.0402   1.0000
  10.500   1.0954   0.03833   0.03043  -0.0405   0.0336   1.0000
  10.750   1.1044   0.04011   0.03232  -0.0388   0.0291   1.0000
  11.000   1.1135   0.04186   0.03406  -0.0376   0.0245   1.0000
  11.250   1.1291   0.04361   0.03594  -0.0362   0.0218   1.0000
  11.500   1.1508   0.04506   0.03752  -0.0353   0.0201   1.0000
  11.750   1.1758   0.04669   0.03932  -0.0346   0.0188   1.0000
  12.000   1.2013   0.04871   0.04155  -0.0341   0.0181   1.0000
  12.250   1.2249   0.05136   0.04449  -0.0334   0.0177   1.0000
  12.500   1.2427   0.05490   0.04842  -0.0324   0.0179   1.0000
  12.750   1.2456   0.05947   0.05349  -0.0306   0.0185   1.0000
  13.000   1.2387   0.06436   0.05881  -0.0286   0.0193   1.0000
  13.250   1.2270   0.06924   0.06404  -0.0268   0.0200   1.0000
  13.500   1.2121   0.07408   0.06917  -0.0254   0.0205   1.0000
  13.750   1.1952   0.07898   0.07434  -0.0245   0.0208   1.0000
  14.000   1.1760   0.08427   0.07987  -0.0241   0.0212   1.0000
  14.250   1.1559   0.08977   0.08559  -0.0242   0.0214   1.0000
  14.500   1.1353   0.09562   0.09164  -0.0251   0.0218   1.0000
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