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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 50,000
Max Cl/Cd: 22.58 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-50000-n5.txt
Download as CSV file: xf-fx74130wp2mod-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3337   0.15163   0.14492  -0.0538   1.0000   0.0789
 -12.500  -0.3438   0.15095   0.14436  -0.0538   1.0000   0.0792
 -12.250  -0.3571   0.15057   0.14409  -0.0528   1.0000   0.0794
 -12.000  -0.3380   0.14418   0.13769  -0.0488   1.0000   0.0818
 -11.750  -0.3422   0.14252   0.13609  -0.0464   1.0000   0.0834
 -11.500  -0.3484   0.14105   0.13467  -0.0443   1.0000   0.0852
 -11.250  -0.3553   0.13960   0.13327  -0.0426   1.0000   0.0869
 -11.000  -0.3529   0.13664   0.13034  -0.0449   0.9966   0.0902
 -10.750  -0.3578   0.13454   0.12829  -0.0494   0.9915   0.0927
 -10.500  -0.3634   0.13221   0.12602  -0.0543   0.9866   0.0933
 -10.250  -0.3356   0.12586   0.11961  -0.0524   0.9850   0.0965
 -10.000  -0.3264   0.12248   0.11622  -0.0538   0.9813   0.1016
  -9.750  -0.3319   0.12009   0.11389  -0.0578   0.9764   0.1062
  -9.500  -0.3385   0.11754   0.11140  -0.0633   0.9719   0.1072
  -9.250  -0.3100   0.11228   0.10608  -0.0608   0.9705   0.1139
  -9.000  -0.3175   0.10995   0.10381  -0.0636   0.9650   0.1199
  -8.750  -0.3158   0.10625   0.10016  -0.0663   0.9609   0.1233
  -8.500  -0.2994   0.10261   0.09645  -0.0669   0.9585   0.1297
  -8.250  -0.3241   0.10101   0.09500  -0.0707   0.9507   0.1351
  -8.000  -0.3060   0.09667   0.09060  -0.0702   0.9482   0.1393
  -7.750  -0.2203   0.07544   0.06950  -0.0821   0.9293   0.0605
  -7.250  -0.3142   0.08085   0.07460  -0.0832   0.9305   0.0615
  -7.000  -0.3221   0.07806   0.07179  -0.0820   0.9235   0.0591
  -6.750  -0.3237   0.07310   0.06647  -0.0851   0.9175   0.0510
  -6.500  -0.3229   0.07020   0.06351  -0.0837   0.9118   0.0498
  -6.250  -0.3174   0.06695   0.06013  -0.0835   0.9066   0.0482
  -6.000  -0.3035   0.06301   0.05588  -0.0851   0.9027   0.0462
  -5.750  -0.3044   0.06032   0.05298  -0.0827   0.8959   0.0450
  -5.500  -0.2899   0.05673   0.04899  -0.0831   0.8913   0.0431
  -5.250  -0.2720   0.05315   0.04485  -0.0833   0.8871   0.0414
  -5.000  -0.2621   0.05068   0.04185  -0.0813   0.8809   0.0402
  -4.750  -0.2372   0.04816   0.03878  -0.0815   0.8770   0.0396
  -4.500  -0.2104   0.04568   0.03581  -0.0820   0.8737   0.0394
  -4.250  -0.1977   0.04390   0.03370  -0.0799   0.8675   0.0395
  -4.000  -0.1706   0.04175   0.03114  -0.0802   0.8638   0.0398
  -3.750  -0.1387   0.03971   0.02882  -0.0813   0.8611   0.0417
  -3.500  -0.1245   0.03882   0.02772  -0.0793   0.8550   0.0449
  -3.250  -0.0972   0.03769   0.02629  -0.0791   0.8508   0.0481
  -3.000  -0.0638   0.03653   0.02479  -0.0793   0.8480   0.0507
  -2.750  -0.0454   0.03582   0.02393  -0.0773   0.8428   0.0530
  -2.500  -0.0237   0.03513   0.02316  -0.0763   0.8380   0.0584
  -2.250   0.0055   0.03439   0.02228  -0.0765   0.8346   0.0713
  -2.000   0.1451   0.03110   0.02208  -0.0890   0.8434   0.9861
  -1.750   0.1960   0.03117   0.02157  -0.0945   0.8399   1.0000
  -1.500   0.2172   0.03133   0.02140  -0.0940   0.8351   1.0000
  -1.250   0.2150   0.03175   0.02166  -0.0896   0.8271   1.0000
  -1.000   0.2317   0.03200   0.02167  -0.0883   0.8219   1.0000
  -0.750   0.2335   0.03241   0.02193  -0.0845   0.8148   1.0000
  -0.500   0.2442   0.03272   0.02207  -0.0821   0.8088   1.0000
  -0.250   0.2553   0.03306   0.02225  -0.0799   0.8032   1.0000
   0.000   0.2547   0.03349   0.02257  -0.0757   0.7959   1.0000
   0.250   0.2781   0.03375   0.02263  -0.0755   0.7923   1.0000
   0.500   0.2656   0.03428   0.02310  -0.0695   0.7833   1.0000
   0.750   0.2864   0.03459   0.02326  -0.0688   0.7794   1.0000
   1.250   0.3006   0.03558   0.02405  -0.0634   0.7673   1.0000
   1.500   0.3282   0.03595   0.02428  -0.0639   0.7643   1.0000
   2.000   0.3507   0.03722   0.02539  -0.0605   0.7526   1.0000
   2.250   0.3672   0.03787   0.02597  -0.0596   0.7477   1.0000
   2.500   0.3813   0.03858   0.02664  -0.0585   0.7419   1.0000
   2.750   0.4075   0.03913   0.02713  -0.0590   0.7384   1.0000
   3.000   0.4212   0.03994   0.02791  -0.0579   0.7329   1.0000
   3.250   0.4394   0.04067   0.02863  -0.0575   0.7276   1.0000
   3.500   0.4670   0.04125   0.02919  -0.0581   0.7243   1.0000
   3.750   0.4778   0.04220   0.03017  -0.0568   0.7180   1.0000
   4.000   0.4995   0.04292   0.03090  -0.0568   0.7132   1.0000
   4.250   0.5292   0.04346   0.03148  -0.0577   0.7100   1.0000
   4.500   0.5367   0.04453   0.03258  -0.0561   0.7021   1.0000
   4.750   0.5642   0.04510   0.03325  -0.0567   0.6979   1.0000
   5.000   0.5776   0.04604   0.03425  -0.0557   0.6907   1.0000
   5.250   0.6026   0.04664   0.03493  -0.0560   0.6854   1.0000
   5.500   0.6202   0.04748   0.03586  -0.0555   0.6787   1.0000
   5.750   0.6425   0.04816   0.03665  -0.0555   0.6724   1.0000
   6.000   0.6620   0.04896   0.03755  -0.0551   0.6657   1.0000
   6.250   0.6840   0.04962   0.03842  -0.0550   0.6589   1.0000
   6.500   0.7017   0.05046   0.03939  -0.0545   0.6510   1.0000
   6.750   0.7284   0.05088   0.04000  -0.0547   0.6444   1.0000
   7.000   0.7436   0.05173   0.04100  -0.0539   0.6346   1.0000
   7.250   0.7792   0.05159   0.04116  -0.0546   0.6290   1.0000
   7.500   0.7931   0.05240   0.04215  -0.0535   0.6175   1.0000
   7.750   0.8112   0.05295   0.04292  -0.0527   0.6063   1.0000
   8.000   0.8344   0.05313   0.04334  -0.0521   0.5955   1.0000
   8.250   0.8736   0.05208   0.04269  -0.0522   0.5873   1.0000
   8.500   0.8967   0.05178   0.04268  -0.0511   0.5737   1.0000
   8.750   0.9200   0.05114   0.04235  -0.0496   0.5580   1.0000
   9.000   0.9337   0.05108   0.04256  -0.0475   0.5379   1.0000
   9.250   0.9651   0.04854   0.04039  -0.0452   0.5154   1.0000
   9.500   0.9716   0.04856   0.04064  -0.0423   0.4835   1.0000
   9.750   0.9760   0.04906   0.04142  -0.0397   0.4432   1.0000
  10.000   1.0144   0.04492   0.03690  -0.0357   0.3308   1.0000
  10.250   1.0123   0.04667   0.03777  -0.0325   0.2337   1.0000
  10.500   1.0028   0.04987   0.04050  -0.0305   0.1792   1.0000
  10.750   0.9954   0.05319   0.04344  -0.0289   0.1396   1.0000
  11.000   0.9922   0.05631   0.04630  -0.0277   0.1130   1.0000
  11.250   0.9931   0.05910   0.04900  -0.0265   0.0962   1.0000
  11.500   0.9965   0.06173   0.05156  -0.0254   0.0819   1.0000
  11.750   1.0035   0.06405   0.05392  -0.0244   0.0705   1.0000
  12.000   1.0166   0.06588   0.05584  -0.0231   0.0620   1.0000
  12.250   1.0297   0.06779   0.05773  -0.0222   0.0537   1.0000
  12.500   1.0598   0.06876   0.05909  -0.0207   0.0462   1.0000
  12.750   1.0850   0.07063   0.06117  -0.0198   0.0403   1.0000
  13.000   1.1068   0.07325   0.06419  -0.0190   0.0366   1.0000
  13.250   1.1196   0.07644   0.06766  -0.0184   0.0346   1.0000
  13.500   1.1287   0.08006   0.07139  -0.0182   0.0325   1.0000
  13.750   1.1223   0.08443   0.07614  -0.0179   0.0316   1.0000
  14.000   1.1125   0.08908   0.08118  -0.0180   0.0310   1.0000
  14.250   1.0999   0.09412   0.08657  -0.0187   0.0306   1.0000
  14.500   1.0855   0.09959   0.09236  -0.0199   0.0303   1.0000
  14.750   1.0695   0.10553   0.09857  -0.0217   0.0301   1.0000
  15.000   1.0520   0.11205   0.10534  -0.0244   0.0301   1.0000
  15.250   1.0352   0.11892   0.11241  -0.0277   0.0303   1.0000
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