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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 500,000
Max Cl/Cd: 40.29 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-npl9510-il-500000.txt
Download as CSV file: xf-npl9510-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9510 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -1.0603   0.10571   0.10229  -0.0258   1.0000   0.0228
 -17.250  -1.0858   0.09685   0.09323  -0.0310   1.0000   0.0228
 -17.000  -1.1032   0.08985   0.08607  -0.0350   1.0000   0.0229
 -16.750  -1.1169   0.08378   0.07986  -0.0384   1.0000   0.0229
 -16.500  -1.1278   0.07839   0.07433  -0.0413   1.0000   0.0231
 -16.250  -1.1356   0.07367   0.06949  -0.0438   1.0000   0.0233
 -16.000  -1.1418   0.06938   0.06507  -0.0459   1.0000   0.0234
 -15.750  -1.1470   0.06536   0.06093  -0.0478   1.0000   0.0237
 -15.500  -1.1518   0.06157   0.05702  -0.0495   1.0000   0.0239
 -15.250  -1.1558   0.05808   0.05339  -0.0508   1.0000   0.0241
 -15.000  -1.1584   0.05481   0.04999  -0.0520   1.0000   0.0243
 -14.750  -1.1597   0.05177   0.04681  -0.0529   1.0000   0.0246
 -14.500  -1.1592   0.04898   0.04388  -0.0536   1.0000   0.0248
 -14.250  -1.1572   0.04641   0.04118  -0.0542   1.0000   0.0250
 -14.000  -1.1537   0.04404   0.03868  -0.0547   1.0000   0.0252
 -13.750  -1.1489   0.04185   0.03636  -0.0551   1.0000   0.0254
 -13.500  -1.1429   0.03983   0.03422  -0.0554   1.0000   0.0256
 -13.250  -1.1361   0.03784   0.03217  -0.0542   1.0000   0.0260
 -13.000  -1.1280   0.03614   0.03044  -0.0537   1.0000   0.0265
 -12.750  -1.1193   0.03454   0.02882  -0.0535   1.0000   0.0269
 -12.500  -1.1104   0.03301   0.02725  -0.0533   1.0000   0.0273
 -12.250  -1.1022   0.03155   0.02574  -0.0528   1.0000   0.0278
 -12.000  -1.0959   0.03015   0.02429  -0.0517   1.0000   0.0282
 -11.750  -1.0940   0.02885   0.02294  -0.0498   1.0000   0.0285
 -11.500  -1.0877   0.02755   0.02158  -0.0486   1.0000   0.0289
 -11.250  -1.0783   0.02630   0.02026  -0.0479   1.0000   0.0294
 -11.000  -1.0661   0.02513   0.01900  -0.0475   1.0000   0.0298
 -10.750  -1.0517   0.02401   0.01781  -0.0473   1.0000   0.0302
 -10.500  -1.0399   0.02241   0.01618  -0.0469   1.0000   0.0310
 -10.250  -1.0229   0.02136   0.01511  -0.0467   1.0000   0.0318
 -10.000  -1.0038   0.02049   0.01421  -0.0466   1.0000   0.0327
  -9.750  -0.9832   0.01973   0.01339  -0.0464   1.0000   0.0339
  -9.500  -0.9615   0.01908   0.01268  -0.0463   1.0000   0.0350
  -9.250  -0.9397   0.01802   0.01158  -0.0467   1.0000   0.0365
  -9.000  -0.9163   0.01725   0.01081  -0.0470   1.0000   0.0383
  -8.750  -0.8922   0.01665   0.01016  -0.0472   1.0000   0.0403
  -8.500  -0.8671   0.01589   0.00937  -0.0477   1.0000   0.0429
  -8.250  -0.8416   0.01528   0.00876  -0.0481   1.0000   0.0464
  -8.000  -0.8154   0.01465   0.00812  -0.0486   1.0000   0.0512
  -7.750  -0.7888   0.01408   0.00759  -0.0492   1.0000   0.0583
  -7.500  -0.7615   0.01349   0.00707  -0.0499   1.0000   0.0706
  -7.250  -0.7335   0.01294   0.00663  -0.0507   1.0000   0.0896
  -7.000  -0.7054   0.01253   0.00630  -0.0514   1.0000   0.1082
  -6.750  -0.6773   0.01219   0.00602  -0.0520   1.0000   0.1247
  -6.500  -0.6487   0.01184   0.00574  -0.0527   1.0000   0.1421
  -6.250  -0.6199   0.01150   0.00547  -0.0535   1.0000   0.1612
  -6.000  -0.5906   0.01115   0.00521  -0.0543   1.0000   0.1838
  -5.750  -0.5569   0.01061   0.00487  -0.0563   0.9996   0.2246
  -5.250  -0.4868   0.00945   0.00431  -0.0609   0.9987   0.3627
  -5.000  -0.4530   0.00927   0.00425  -0.0624   0.9978   0.4001
  -4.750  -0.4195   0.00921   0.00423  -0.0638   0.9968   0.4270
  -4.500  -0.3859   0.00920   0.00428  -0.0651   0.9958   0.4500
  -4.250  -0.3521   0.00922   0.00431  -0.0664   0.9949   0.4645
  -4.000  -0.3181   0.00927   0.00434  -0.0677   0.9941   0.4760
  -3.750  -0.2869   0.00929   0.00437  -0.0685   0.9923   0.4854
  -3.500  -0.2545   0.00931   0.00437  -0.0695   0.9906   0.4926
  -3.250  -0.2217   0.00934   0.00442  -0.0705   0.9890   0.4997
  -3.000  -0.1886   0.00940   0.00444  -0.0717   0.9876   0.5069
  -2.750  -0.1553   0.00941   0.00451  -0.0728   0.9864   0.5126
  -2.500  -0.1215   0.00947   0.00457  -0.0741   0.9854   0.5188
  -2.250  -0.0873   0.00953   0.00466  -0.0754   0.9844   0.5268
  -2.000  -0.0550   0.00963   0.00480  -0.0763   0.9828   0.5349
  -1.750  -0.0261   0.00970   0.00487  -0.0765   0.9800   0.5415
  -1.500   0.0060   0.00972   0.00497  -0.0773   0.9778   0.5470
  -1.250   0.0523   0.00951   0.00479  -0.0809   0.9738   0.5523
  -1.000   0.1255   0.00857   0.00386  -0.0893   0.9620   0.5573
  -0.750   0.1655   0.00814   0.00351  -0.0912   0.9527   0.5613
  -0.500   0.1988   0.00789   0.00331  -0.0916   0.9432   0.5650
  -0.250   0.2255   0.00770   0.00314  -0.0906   0.9259   0.5690
   0.000   0.2518   0.00755   0.00294  -0.0895   0.8960   0.5729
   0.250   0.2760   0.00756   0.00273  -0.0877   0.8167   0.5763
   0.500   0.2780   0.01052   0.00319  -0.0829   0.2125   0.5792
   0.750   0.3020   0.01138   0.00348  -0.0823   0.0760   0.5827
   1.000   0.3295   0.01171   0.00373  -0.0821   0.0621   0.5865
   1.250   0.3576   0.01196   0.00395  -0.0820   0.0566   0.5904
   1.500   0.3846   0.01231   0.00428  -0.0817   0.0523   0.5940
   1.750   0.4123   0.01254   0.00456  -0.0815   0.0501   0.5973
   2.000   0.4398   0.01281   0.00483  -0.0812   0.0476   0.6010
   2.250   0.4665   0.01324   0.00523  -0.0809   0.0453   0.6050
   2.500   0.4932   0.01373   0.00572  -0.0805   0.0438   0.6087
   2.750   0.5204   0.01404   0.00607  -0.0802   0.0423   0.6121
   3.000   0.5474   0.01437   0.00643  -0.0799   0.0407   0.6155
   3.250   0.5741   0.01481   0.00685  -0.0796   0.0391   0.6194
   3.500   0.5997   0.01572   0.00775  -0.0791   0.0378   0.6235
   3.750   0.6273   0.01613   0.00821  -0.0788   0.0369   0.6273
   4.000   0.6543   0.01662   0.00879  -0.0784   0.0358   0.6309
   4.250   0.6814   0.01708   0.00928  -0.0781   0.0345   0.6346
   4.500   0.7083   0.01758   0.00978  -0.0779   0.0334   0.6389
   4.750   0.7347   0.01895   0.01116  -0.0776   0.0324   0.6431
   5.000   0.7617   0.01951   0.01190  -0.0771   0.0317   0.6471
   5.250   0.7883   0.02041   0.01297  -0.0766   0.0309   0.6511
   5.500   0.8147   0.02146   0.01417  -0.0761   0.0301   0.6553
   5.750   0.8407   0.02245   0.01527  -0.0757   0.0294   0.6598
   6.000   0.8666   0.02308   0.01594  -0.0753   0.0287   0.6642
   6.250   0.8913   0.02420   0.01712  -0.0749   0.0280   0.6687
   6.500   0.9135   0.02634   0.01962  -0.0737   0.0273   0.6733
   6.750   0.9342   0.02878   0.02248  -0.0722   0.0269   0.6778
   7.000   0.9506   0.03229   0.02649  -0.0702   0.0268   0.6817
   7.250   0.9630   0.03636   0.03103  -0.0678   0.0270   0.6857
   7.500   0.9746   0.04018   0.03511  -0.0659   0.0275   0.6904
   8.500   0.9081   0.07664   0.07374  -0.0529   0.0304   0.7007
   8.750   0.8928   0.08173   0.07897  -0.0522   0.0300   0.7043
   9.000   0.8706   0.08719   0.08452  -0.0525   0.0298   0.7082
   9.250   0.8473   0.09478   0.09217  -0.0574   0.0297   0.7114
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