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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.48 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-1000000-n5.txt
Download as CSV file: xf-fx74130wp2mod-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1822   0.08555   0.08278  -0.0969   0.7742   0.0045
  -8.250  -0.2347   0.05032   0.04754  -0.1138   0.7613   0.0051
  -6.500  -0.1982   0.02229   0.01797  -0.1049   0.7493   0.0046
  -6.250  -0.1837   0.01861   0.01384  -0.1033   0.7479   0.0045
  -6.000  -0.1631   0.01636   0.01124  -0.1024   0.7466   0.0045
  -5.750  -0.1401   0.01468   0.00928  -0.1017   0.7453   0.0045
  -5.500  -0.1154   0.01359   0.00801  -0.1014   0.7439   0.0046
  -5.250  -0.0901   0.01271   0.00699  -0.1012   0.7425   0.0046
  -5.000  -0.0645   0.01200   0.00616  -0.1010   0.7411   0.0047
  -4.750  -0.0385   0.01144   0.00551  -0.1008   0.7395   0.0048
  -4.500  -0.0147   0.01044   0.00438  -0.1003   0.7380   0.0052
  -4.250   0.0116   0.01004   0.00391  -0.1003   0.7365   0.0056
  -4.000   0.0386   0.00975   0.00361  -0.1004   0.7350   0.0060
  -3.750   0.0657   0.00946   0.00331  -0.1005   0.7334   0.0064
  -3.500   0.0930   0.00919   0.00300  -0.1006   0.7316   0.0067
  -3.250   0.1204   0.00894   0.00272  -0.1008   0.7297   0.0070
  -3.000   0.1480   0.00873   0.00248  -0.1010   0.7277   0.0073
  -2.750   0.1757   0.00857   0.00229  -0.1012   0.7257   0.0078
  -2.500   0.2033   0.00836   0.00203  -0.1013   0.7237   0.0086
  -2.250   0.2312   0.00819   0.00184  -0.1015   0.7215   0.0099
  -2.000   0.2593   0.00804   0.00170  -0.1018   0.7189   0.0136
  -1.750   0.2871   0.00784   0.00159  -0.1020   0.7162   0.0357
  -1.500   0.3147   0.00762   0.00148  -0.1023   0.7134   0.0782
  -1.250   0.3409   0.00701   0.00137  -0.1027   0.7107   0.2471
  -1.000   0.3666   0.00607   0.00124  -0.1033   0.7078   0.5196
  -0.750   0.3926   0.00543   0.00132  -0.1034   0.7043   0.7494
  -0.500   0.4208   0.00549   0.00140  -0.1035   0.7004   0.7804
  -0.250   0.4491   0.00555   0.00143  -0.1037   0.6965   0.7935
   0.000   0.4776   0.00561   0.00147  -0.1039   0.6920   0.8013
   0.250   0.5060   0.00565   0.00148  -0.1042   0.6863   0.8069
   0.500   0.5338   0.00570   0.00152  -0.1043   0.6805   0.8117
   0.750   0.5620   0.00575   0.00154  -0.1046   0.6734   0.8159
   1.000   0.5903   0.00580   0.00155  -0.1049   0.6666   0.8186
   1.250   0.6183   0.00584   0.00156  -0.1051   0.6588   0.8202
   1.500   0.6461   0.00589   0.00158  -0.1053   0.6513   0.8214
   1.750   0.6736   0.00595   0.00161  -0.1055   0.6434   0.8223
   2.000   0.7014   0.00601   0.00166  -0.1057   0.6361   0.8231
   2.500   0.7565   0.00617   0.00177  -0.1061   0.6219   0.8249
   3.000   0.8113   0.00635   0.00193  -0.1065   0.6080   0.8266
   3.250   0.8381   0.00646   0.00202  -0.1065   0.6002   0.8274
   3.500   0.8645   0.00659   0.00212  -0.1066   0.5891   0.8282
   3.750   0.8901   0.00677   0.00226  -0.1064   0.5747   0.8292
   4.000   0.9151   0.00696   0.00240  -0.1061   0.5589   0.8302
   4.250   0.9401   0.00716   0.00255  -0.1059   0.5405   0.8310
   4.500   0.9648   0.00737   0.00270  -0.1056   0.5225   0.8318
   4.750   0.9885   0.00762   0.00290  -0.1051   0.5010   0.8325
   5.000   1.0059   0.00818   0.00321  -0.1035   0.4422   0.8334
   5.250   1.0111   0.00933   0.00387  -0.0998   0.3442   0.8347
   5.500   1.0229   0.01011   0.00438  -0.0973   0.2861   0.8358
   5.750   1.0354   0.01080   0.00486  -0.0949   0.2394   0.8370
   6.000   1.0474   0.01146   0.00533  -0.0924   0.1984   0.8384
   6.250   1.0540   0.01211   0.00583  -0.0888   0.1589   0.8400
   6.500   1.0594   0.01284   0.00639  -0.0852   0.1222   0.8415
   6.750   1.0699   0.01344   0.00691  -0.0825   0.1012   0.8429
   7.000   1.0751   0.01429   0.00761  -0.0792   0.0702   0.8445
   7.250   1.0816   0.01518   0.00837  -0.0763   0.0457   0.8459
   7.750   1.1059   0.01658   0.00970  -0.0725   0.0250   0.8486
   8.000   1.1207   0.01719   0.01034  -0.0710   0.0205   0.8500
   8.250   1.1348   0.01786   0.01102  -0.0696   0.0173   0.8515
   8.500   1.1498   0.01850   0.01169  -0.0682   0.0145   0.8532
   8.750   1.1640   0.01921   0.01241  -0.0668   0.0116   0.8550
   9.000   1.1775   0.01998   0.01319  -0.0654   0.0088   0.8568
   9.250   1.1901   0.02083   0.01404  -0.0639   0.0062   0.8585
   9.500   1.2031   0.02167   0.01491  -0.0625   0.0046   0.8602
   9.750   1.2156   0.02256   0.01584  -0.0611   0.0037   0.8619
  10.000   1.2287   0.02341   0.01677  -0.0598   0.0033   0.8640
  10.250   1.2413   0.02431   0.01773  -0.0584   0.0030   0.8663
  10.500   1.2542   0.02522   0.01870  -0.0572   0.0028   0.8688
  10.750   1.2662   0.02620   0.01975  -0.0559   0.0027   0.8714
  11.000   1.2781   0.02721   0.02081  -0.0546   0.0024   0.8742
  11.250   1.2883   0.02835   0.02203  -0.0532   0.0022   0.8777
  11.500   1.2966   0.02967   0.02345  -0.0516   0.0020   0.8820
  11.750   1.3046   0.03102   0.02490  -0.0501   0.0019   0.8870
  12.000   1.3143   0.03225   0.02623  -0.0488   0.0019   0.8936
  12.500   1.3307   0.03474   0.02899  -0.0457   0.0019   0.9291
  13.000   1.3505   0.03763   0.03210  -0.0442   0.0018   1.0000
  13.250   1.3577   0.03936   0.03392  -0.0431   0.0018   1.0000
  13.500   1.3660   0.04102   0.03567  -0.0423   0.0018   1.0000
  13.750   1.3721   0.04294   0.03768  -0.0414   0.0017   1.0000
  14.000   1.3800   0.04471   0.03954  -0.0407   0.0017   1.0000
  14.250   1.3862   0.04672   0.04164  -0.0400   0.0017   1.0000
  14.500   1.3913   0.04890   0.04393  -0.0393   0.0016   1.0000
  14.750   1.3963   0.05113   0.04625  -0.0388   0.0016   1.0000
  15.000   1.4001   0.05357   0.04880  -0.0383   0.0015   1.0000
  15.250   1.4037   0.05608   0.05142  -0.0380   0.0015   1.0000
  15.500   1.4066   0.05876   0.05423  -0.0377   0.0015   1.0000
  15.750   1.4084   0.06162   0.05721  -0.0376   0.0015   1.0000
  16.000   1.4091   0.06470   0.06041  -0.0376   0.0014   1.0000
  16.250   1.4098   0.06787   0.06369  -0.0377   0.0014   1.0000
  16.500   1.4098   0.07122   0.06715  -0.0381   0.0014   1.0000
  16.750   1.4068   0.07507   0.07114  -0.0385   0.0014   1.0000
  17.000   1.4058   0.07870   0.07490  -0.0392   0.0013   1.0000
  17.250   1.4012   0.08299   0.07932  -0.0401   0.0013   1.0000
  17.500   1.3972   0.08731   0.08377  -0.0412   0.0013   1.0000
  17.750   1.3897   0.09229   0.08890  -0.0426   0.0013   1.0000
  18.000   1.3829   0.09730   0.09403  -0.0443   0.0012   1.0000
  18.250   1.3734   0.10291   0.09980  -0.0464   0.0012   1.0000
  18.500   1.3661   0.10831   0.10532  -0.0486   0.0012   1.0000
  18.750   1.3535   0.11486   0.11203  -0.0515   0.0012   1.0000
  19.000   1.3426   0.12128   0.11860  -0.0547   0.0012   1.0000
  19.250   1.3299   0.12828   0.12574  -0.0584   0.0012   1.0000
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