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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 100,000
Max Cl/Cd: 44.98 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-100000-n5.txt
Download as CSV file: xf-fx74130wp2mod-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2 MOD                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1758   0.09745   0.09234  -0.0953   0.9177   0.0480
  -9.750  -0.1718   0.09397   0.08887  -0.0983   0.9141   0.0494
  -9.500  -0.1769   0.09080   0.08574  -0.1041   0.9086   0.0514
  -9.250  -0.1791   0.08684   0.08180  -0.1094   0.9039   0.0518
  -9.000  -0.1844   0.08285   0.07781  -0.1139   0.8988   0.0519
  -8.500  -0.1011   0.06193   0.05707  -0.1063   0.8850   0.0343
  -8.000  -0.1318   0.05078   0.04580  -0.1148   0.8764   0.0269
  -7.500  -0.1806   0.05876   0.05336  -0.1180   0.8759   0.0261
  -7.250  -0.1809   0.05589   0.05036  -0.1173   0.8719   0.0253
  -7.000  -0.1806   0.05310   0.04743  -0.1162   0.8671   0.0247
  -6.750  -0.1758   0.05004   0.04416  -0.1154   0.8631   0.0239
  -6.500  -0.1690   0.04694   0.04078  -0.1144   0.8594   0.0232
  -6.250  -0.1640   0.04432   0.03790  -0.1125   0.8540   0.0225
  -6.000  -0.1527   0.04140   0.03463  -0.1112   0.8501   0.0218
  -5.750  -0.1368   0.03850   0.03131  -0.1101   0.8472   0.0217
  -5.500  -0.1256   0.03666   0.02916  -0.1081   0.8422   0.0219
  -5.250  -0.1085   0.03491   0.02707  -0.1068   0.8382   0.0234
  -5.000  -0.0867   0.03296   0.02468  -0.1060   0.8352   0.0248
  -4.750  -0.0626   0.03098   0.02228  -0.1054   0.8328   0.0250
  -4.500  -0.0470   0.02969   0.02070  -0.1033   0.8275   0.0251
  -4.250  -0.0234   0.02818   0.01886  -0.1024   0.8240   0.0254
  -4.000   0.0033   0.02680   0.01722  -0.1020   0.8214   0.0258
  -3.750   0.0315   0.02556   0.01576  -0.1017   0.8194   0.0265
  -3.500   0.0464   0.02502   0.01514  -0.0995   0.8135   0.0273
  -3.250   0.0682   0.02399   0.01408  -0.0985   0.8099   0.0287
  -3.000   0.0931   0.02325   0.01330  -0.0982   0.8072   0.0328
  -2.750   0.1145   0.02289   0.01279  -0.0971   0.8034   0.0387
  -2.500   0.1318   0.02246   0.01233  -0.0955   0.7981   0.0456
  -2.250   0.1556   0.02171   0.01174  -0.0947   0.7948   0.0854
  -2.000   0.1604   0.01934   0.01183  -0.0905   0.7922   0.6288
  -1.750   0.1562   0.02020   0.01298  -0.0826   0.7846   0.8094
  -1.500   0.1576   0.02072   0.01352  -0.0742   0.7808   0.8826
  -1.250   0.2156   0.02098   0.01350  -0.0770   0.7804   0.9384
  -1.000   0.2549   0.02089   0.01316  -0.0793   0.7786   0.9460
  -0.750   0.2809   0.02113   0.01327  -0.0798   0.7723   0.9525
  -0.500   0.3085   0.02114   0.01311  -0.0802   0.7684   0.9580
  -0.250   0.3472   0.02104   0.01285  -0.0827   0.7661   0.9605
   0.000   0.3841   0.02093   0.01260  -0.0848   0.7643   0.9631
   0.250   0.3987   0.02139   0.01302  -0.0834   0.7562   0.9693
   0.500   0.4304   0.02136   0.01290  -0.0846   0.7532   0.9721
   0.750   0.4658   0.02126   0.01271  -0.0864   0.7512   0.9741
   1.000   0.4846   0.02171   0.01315  -0.0859   0.7434   0.9791
   1.250   0.5127   0.02175   0.01315  -0.0865   0.7400   0.9823
   1.500   0.5450   0.02170   0.01305  -0.0877   0.7378   0.9847
   1.750   0.5636   0.02226   0.01364  -0.0873   0.7303   0.9896
   2.000   0.5914   0.02235   0.01372  -0.0879   0.7266   0.9931
   2.250   0.6229   0.02228   0.01366  -0.0889   0.7243   0.9957
   2.500   0.6273   0.02299   0.01441  -0.0859   0.7157   1.0000
   2.750   0.6423   0.02308   0.01451  -0.0839   0.7121   1.0000
   3.000   0.6550   0.02323   0.01467  -0.0815   0.7082   1.0000
   3.250   0.6431   0.02389   0.01535  -0.0753   0.6992   1.0000
   3.500   0.6676   0.02382   0.01531  -0.0749   0.6970   1.0000
   3.750   0.6587   0.02488   0.01642  -0.0699   0.6871   1.0000
   4.000   0.6863   0.02490   0.01648  -0.0702   0.6848   1.0000
   4.250   0.7173   0.02482   0.01646  -0.0709   0.6831   1.0000
   4.500   0.7151   0.02616   0.01783  -0.0676   0.6729   1.0000
   4.750   0.7456   0.02609   0.01784  -0.0682   0.6709   1.0000
   5.000   0.7774   0.02596   0.01785  -0.0689   0.6692   1.0000
   5.250   0.7822   0.02714   0.01909  -0.0667   0.6587   1.0000
   5.500   0.8165   0.02669   0.01875  -0.0675   0.6569   1.0000
   6.000   0.8565   0.02750   0.01979  -0.0662   0.6444   1.0000
   6.250   0.8935   0.02675   0.01923  -0.0670   0.6420   1.0000
   6.500   0.9057   0.02739   0.01999  -0.0654   0.6314   1.0000
   7.000   0.9737   0.02552   0.01850  -0.0655   0.6161   1.0000
   7.250   1.0000   0.02493   0.01806  -0.0647   0.6029   1.0000
   7.500   1.0268   0.02416   0.01742  -0.0637   0.5844   1.0000
   7.750   1.0534   0.02342   0.01676  -0.0625   0.5585   1.0000
   8.000   1.0652   0.02378   0.01718  -0.0603   0.5291   1.0000
   8.250   1.0728   0.02443   0.01783  -0.0576   0.4880   1.0000
   8.500   1.0825   0.02483   0.01782  -0.0547   0.3916   1.0000
   8.750   1.0752   0.02671   0.01903  -0.0507   0.3043   1.0000
   9.000   1.0654   0.02911   0.02097  -0.0472   0.2360   1.0000
   9.250   1.0596   0.03142   0.02294  -0.0445   0.1790   1.0000
   9.500   1.0574   0.03362   0.02484  -0.0421   0.1314   1.0000
   9.750   1.0578   0.03574   0.02670  -0.0401   0.0941   1.0000
  10.000   1.0610   0.03771   0.02852  -0.0384   0.0709   1.0000
  10.250   1.0655   0.03965   0.03043  -0.0368   0.0580   1.0000
  10.500   1.0709   0.04155   0.03236  -0.0353   0.0486   1.0000
  10.750   1.0746   0.04367   0.03448  -0.0339   0.0420   1.0000
  11.000   1.0819   0.04552   0.03647  -0.0327   0.0359   1.0000
  11.250   1.0855   0.04776   0.03873  -0.0314   0.0315   1.0000
  11.500   1.0935   0.04973   0.04093  -0.0302   0.0278   1.0000
  11.750   1.1004   0.05177   0.04305  -0.0293   0.0245   1.0000
  12.000   1.1077   0.05398   0.04534  -0.0283   0.0219   1.0000
  12.250   1.1204   0.05590   0.04746  -0.0273   0.0200   1.0000
  12.500   1.1343   0.05793   0.04967  -0.0263   0.0185   1.0000
  12.750   1.1468   0.06011   0.05201  -0.0255   0.0174   1.0000
  13.000   1.1545   0.06257   0.05459  -0.0250   0.0161   1.0000
  13.250   1.1635   0.06567   0.05785  -0.0243   0.0150   1.0000
  13.500   1.1680   0.06861   0.06115  -0.0237   0.0142   1.0000
  13.750   1.1697   0.07203   0.06490  -0.0232   0.0135   1.0000
  14.000   1.1683   0.07591   0.06911  -0.0228   0.0132   1.0000
  14.250   1.1628   0.08026   0.07377  -0.0227   0.0130   1.0000
  14.500   1.1538   0.08502   0.07885  -0.0230   0.0128   1.0000
  14.750   1.1421   0.09023   0.08435  -0.0237   0.0128   1.0000
  15.000   1.1279   0.09596   0.09036  -0.0251   0.0127   1.0000
  15.250   1.1128   0.10204   0.09671  -0.0271   0.0127   1.0000
  15.500   1.0955   0.10880   0.10372  -0.0298   0.0127   1.0000
  15.750   1.0776   0.11608   0.11124  -0.0333   0.0128   1.0000
  16.000   1.0586   0.12417   0.11953  -0.0377   0.0129   1.0000
  16.250   1.0389   0.13316   0.12871  -0.0431   0.0131   1.0000
  16.500   1.0191   0.14320   0.13889  -0.0496   0.0133   1.0000
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