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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 200,000
Max Cl/Cd: 75.31 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-200000-n5.txt
Download as CSV file: xf-fx74130wp2-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1209   0.08799   0.08369  -0.0904   0.7862   0.0268
  -8.250  -0.1757   0.06756   0.06304  -0.1134   0.7803   0.0270
  -7.750  -0.1824   0.06155   0.05682  -0.1136   0.7775   0.0271
  -7.250  -0.1860   0.05115   0.04628  -0.1130   0.7747   0.0175
  -7.000  -0.1836   0.04802   0.04304  -0.1125   0.7733   0.0166
  -6.750  -0.1776   0.04474   0.03959  -0.1119   0.7718   0.0157
  -6.500  -0.1696   0.04113   0.03572  -0.1110   0.7704   0.0148
  -6.250  -0.1599   0.03676   0.03095  -0.1095   0.7689   0.0135
  -6.000  -0.1460   0.03228   0.02585  -0.1075   0.7675   0.0124
  -5.750  -0.1260   0.03036   0.02358  -0.1066   0.7663   0.0121
  -5.500  -0.1067   0.02797   0.02080  -0.1057   0.7652   0.0121
  -5.250  -0.0853   0.02591   0.01837  -0.1050   0.7644   0.0121
  -5.000  -0.0626   0.02391   0.01602  -0.1044   0.7635   0.0123
  -4.750  -0.0394   0.02243   0.01433  -0.1039   0.7623   0.0126
  -4.500  -0.0155   0.02146   0.01325  -0.1036   0.7609   0.0135
  -4.250   0.0091   0.02088   0.01256  -0.1034   0.7595   0.0151
  -4.000   0.0342   0.02016   0.01170  -0.1031   0.7580   0.0165
  -3.750   0.0589   0.01926   0.01070  -0.1026   0.7566   0.0169
  -3.500   0.0833   0.01852   0.00989  -0.1021   0.7553   0.0173
  -3.250   0.1076   0.01791   0.00921  -0.1016   0.7542   0.0179
  -3.000   0.1317   0.01730   0.00852  -0.1012   0.7532   0.0189
  -2.750   0.1566   0.01684   0.00799  -0.1010   0.7522   0.0212
  -2.500   0.1826   0.01654   0.00760  -0.1008   0.7513   0.0259
  -2.250   0.2082   0.01611   0.00724  -0.1007   0.7503   0.0528
  -2.000   0.2271   0.01482   0.00708  -0.1005   0.7488   0.3363
  -1.750   0.2316   0.01408   0.00796  -0.0954   0.7468   0.7566
  -1.500   0.2522   0.01454   0.00838  -0.0936   0.7451   0.8105
  -1.250   0.2669   0.01504   0.00887  -0.0900   0.7434   0.8473
  -1.000   0.2801   0.01534   0.00917  -0.0860   0.7417   0.8694
  -0.750   0.3007   0.01545   0.00922  -0.0842   0.7402   0.8807
  -0.500   0.3253   0.01554   0.00920  -0.0838   0.7390   0.8879
  -0.250   0.3505   0.01560   0.00918  -0.0834   0.7380   0.8917
   0.000   0.3768   0.01565   0.00916  -0.0833   0.7371   0.8950
   0.250   0.4043   0.01570   0.00912  -0.0835   0.7362   0.8981
   0.500   0.4242   0.01604   0.00948  -0.0828   0.7330   0.9019
   0.750   0.4463   0.01628   0.00970  -0.0823   0.7307   0.9045
   1.000   0.4705   0.01642   0.00983  -0.0820   0.7286   0.9068
   1.250   0.4962   0.01653   0.00992  -0.0820   0.7269   0.9091
   1.500   0.5233   0.01662   0.00999  -0.0822   0.7255   0.9111
   1.750   0.5516   0.01667   0.01001  -0.0827   0.7243   0.9131
   2.000   0.5808   0.01669   0.01002  -0.0833   0.7232   0.9149
   2.500   0.6202   0.01736   0.01080  -0.0816   0.7158   0.9195
   2.750   0.6455   0.01747   0.01093  -0.0815   0.7135   0.9216
   3.000   0.6735   0.01751   0.01099  -0.0819   0.7118   0.9233
   3.250   0.7028   0.01750   0.01103  -0.0824   0.7104   0.9248
   3.500   0.7333   0.01745   0.01101  -0.0832   0.7093   0.9263
   4.000   0.7696   0.01812   0.01184  -0.0809   0.6996   0.9324
   4.250   0.7998   0.01799   0.01177  -0.0815   0.6977   0.9340
   4.500   0.8325   0.01774   0.01160  -0.0824   0.6962   0.9354
   5.000   0.8734   0.01800   0.01207  -0.0806   0.6854   0.9421
   5.500   0.9224   0.01771   0.01203  -0.0797   0.6746   0.9493
   5.750   0.9595   0.01685   0.01125  -0.0809   0.6698   0.9509
   6.000   0.9758   0.01680   0.01135  -0.0791   0.6590   0.9576
   6.250   0.9968   0.01659   0.01127  -0.0781   0.6464   0.9654
   6.500   1.0196   0.01630   0.01112  -0.0775   0.6299   0.9794
   6.750   1.0298   0.01658   0.01148  -0.0751   0.6074   1.0000
   7.000   1.0829   0.01438   0.00878  -0.0769   0.5158   1.0000
   7.250   1.0774   0.01549   0.00935  -0.0718   0.4383   1.0000
   7.500   1.0676   0.01720   0.01070  -0.0672   0.3782   1.0000
   7.750   1.0602   0.01907   0.01227  -0.0635   0.3231   1.0000
   8.000   1.0570   0.02088   0.01382  -0.0605   0.2727   1.0000
   8.250   1.0549   0.02272   0.01538  -0.0577   0.2216   1.0000
   8.500   1.0546   0.02454   0.01691  -0.0552   0.1720   1.0000
   8.750   1.0567   0.02626   0.01841  -0.0531   0.1266   1.0000
   9.000   1.0611   0.02790   0.01983  -0.0512   0.0905   1.0000
   9.250   1.0684   0.02936   0.02117  -0.0496   0.0664   1.0000
   9.500   1.0770   0.03078   0.02252  -0.0482   0.0498   1.0000
   9.750   1.0867   0.03214   0.02388  -0.0469   0.0397   1.0000
  10.000   1.0958   0.03357   0.02529  -0.0456   0.0317   1.0000
  10.250   1.1067   0.03488   0.02665  -0.0445   0.0256   1.0000
  10.500   1.1163   0.03634   0.02816  -0.0434   0.0211   1.0000
  10.750   1.1260   0.03781   0.02973  -0.0422   0.0180   1.0000
  11.000   1.1313   0.03974   0.03174  -0.0408   0.0150   1.0000
  11.250   1.1427   0.04113   0.03325  -0.0399   0.0127   1.0000
  11.500   1.1524   0.04270   0.03490  -0.0390   0.0112   1.0000
  11.750   1.1578   0.04475   0.03702  -0.0378   0.0101   1.0000
  12.000   1.1633   0.04684   0.03924  -0.0366   0.0095   1.0000
  12.250   1.1710   0.04880   0.04135  -0.0356   0.0089   1.0000
  12.500   1.1788   0.05079   0.04349  -0.0346   0.0085   1.0000
  12.750   1.1866   0.05288   0.04573  -0.0337   0.0080   1.0000
  13.000   1.1946   0.05500   0.04800  -0.0328   0.0077   1.0000
  13.250   1.2023   0.05721   0.05035  -0.0320   0.0074   1.0000
  13.500   1.2093   0.05955   0.05285  -0.0313   0.0071   1.0000
  13.750   1.2153   0.06205   0.05553  -0.0307   0.0070   1.0000
  14.000   1.2195   0.06481   0.05850  -0.0301   0.0068   1.0000
  14.250   1.2220   0.06785   0.06173  -0.0297   0.0066   1.0000
  14.500   1.2226   0.07117   0.06527  -0.0293   0.0065   1.0000
  14.750   1.2205   0.07496   0.06927  -0.0291   0.0064   1.0000
  15.000   1.2156   0.07919   0.07374  -0.0291   0.0063   1.0000
  15.250   1.2078   0.08391   0.07872  -0.0295   0.0063   1.0000
  15.500   1.1969   0.08921   0.08427  -0.0303   0.0062   1.0000
  15.750   1.1844   0.09492   0.09023  -0.0316   0.0062   1.0000
  16.000   1.1714   0.10091   0.09645  -0.0335   0.0061   1.0000
  16.250   1.1575   0.10734   0.10313  -0.0361   0.0061   1.0000
  16.500   1.1427   0.11428   0.11030  -0.0392   0.0061   1.0000
  16.750   1.1274   0.12172   0.11795  -0.0431   0.0061   1.0000
  17.000   1.1115   0.12977   0.12621  -0.0477   0.0061   1.0000
  17.250   1.0954   0.13835   0.13496  -0.0529   0.0061   1.0000
  17.500   0.8263   0.15639   0.15401  -0.0625   0.0077   1.0000
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