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N-22 (n22-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 500,000
Max Cl/Cd: 94.56 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n22-il-500000-n5.txt
Download as CSV file: xf-n22-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-22                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.9035   0.03928   0.03606  -0.0926   0.9999   0.0226
 -15.000  -0.9201   0.03558   0.03213  -0.0927   0.9999   0.0228
 -14.750  -0.9252   0.03320   0.02955  -0.0911   0.9999   0.0231
 -14.500  -0.9265   0.03138   0.02752  -0.0888   0.9999   0.0234
 -14.250  -0.9067   0.02941   0.02531  -0.0900   0.9968   0.0238
 -14.000  -0.8808   0.02811   0.02394  -0.0913   0.9942   0.0242
 -13.750  -0.8538   0.02720   0.02296  -0.0922   0.9913   0.0246
 -13.500  -0.8260   0.02635   0.02204  -0.0931   0.9882   0.0251
 -13.250  -0.7973   0.02548   0.02107  -0.0942   0.9854   0.0256
 -13.000  -0.7690   0.02454   0.02000  -0.0951   0.9826   0.0261
 -12.750  -0.7436   0.02354   0.01885  -0.0955   0.9778   0.0267
 -12.500  -0.7162   0.02251   0.01765  -0.0961   0.9739   0.0273
 -12.250  -0.6889   0.02162   0.01657  -0.0966   0.9697   0.0278
 -12.000  -0.6631   0.02087   0.01566  -0.0965   0.9640   0.0282
 -11.750  -0.6373   0.01975   0.01445  -0.0967   0.9593   0.0287
 -11.500  -0.6124   0.01911   0.01375  -0.0964   0.9528   0.0292
 -11.250  -0.5861   0.01860   0.01317  -0.0961   0.9467   0.0297
 -11.000  -0.5603   0.01807   0.01257  -0.0958   0.9406   0.0302
 -10.750  -0.5352   0.01750   0.01190  -0.0953   0.9331   0.0307
 -10.500  -0.5096   0.01692   0.01122  -0.0948   0.9266   0.0311
 -10.250  -0.4844   0.01638   0.01058  -0.0942   0.9183   0.0317
 -10.000  -0.4586   0.01589   0.00998  -0.0937   0.9111   0.0322
  -9.750  -0.4327   0.01543   0.00941  -0.0932   0.9021   0.0328
  -9.500  -0.4066   0.01497   0.00883  -0.0927   0.8939   0.0331
  -9.250  -0.3807   0.01445   0.00822  -0.0922   0.8845   0.0335
  -9.000  -0.3549   0.01389   0.00760  -0.0918   0.8754   0.0341
  -8.750  -0.3285   0.01348   0.00713  -0.0913   0.8656   0.0347
  -8.500  -0.3016   0.01314   0.00672  -0.0910   0.8557   0.0353
  -8.250  -0.2746   0.01283   0.00633  -0.0906   0.8460   0.0359
  -8.000  -0.2474   0.01254   0.00598  -0.0903   0.8354   0.0367
  -7.750  -0.2200   0.01228   0.00564  -0.0900   0.8252   0.0376
  -7.500  -0.1927   0.01202   0.00528  -0.0897   0.8149   0.0383
  -7.250  -0.1651   0.01177   0.00495  -0.0894   0.8040   0.0390
  -7.000  -0.1376   0.01150   0.00461  -0.0891   0.7936   0.0397
  -6.750  -0.1103   0.01123   0.00427  -0.0889   0.7829   0.0409
  -6.500  -0.0825   0.01102   0.00402  -0.0887   0.7717   0.0421
  -6.250  -0.0546   0.01085   0.00379  -0.0885   0.7606   0.0435
  -6.000  -0.0269   0.01071   0.00356  -0.0883   0.7483   0.0450
  -5.750   0.0010   0.01059   0.00336  -0.0881   0.7355   0.0465
  -5.500   0.0290   0.01039   0.00314  -0.0880   0.7244   0.0493
  -5.250   0.0571   0.01026   0.00297  -0.0879   0.7150   0.0521
  -5.000   0.0854   0.01016   0.00281  -0.0878   0.7053   0.0548
  -4.750   0.1136   0.01001   0.00265  -0.0877   0.6965   0.0595
  -4.500   0.1418   0.00991   0.00252  -0.0877   0.6871   0.0647
  -4.250   0.1701   0.00979   0.00241  -0.0877   0.6776   0.0737
  -4.000   0.1982   0.00969   0.00232  -0.0876   0.6682   0.0866
  -3.750   0.2266   0.00959   0.00225  -0.0876   0.6587   0.1016
  -3.500   0.2548   0.00952   0.00218  -0.0876   0.6489   0.1160
  -3.250   0.2830   0.00946   0.00213  -0.0876   0.6379   0.1302
  -3.000   0.3112   0.00940   0.00208  -0.0876   0.6269   0.1461
  -2.750   0.3393   0.00934   0.00205  -0.0876   0.6165   0.1653
  -2.500   0.3673   0.00928   0.00202  -0.0876   0.6049   0.1901
  -2.250   0.3952   0.00920   0.00200  -0.0876   0.5924   0.2213
  -2.000   0.4229   0.00912   0.00200  -0.0877   0.5790   0.2638
  -1.750   0.4503   0.00897   0.00202  -0.0877   0.5657   0.3354
  -1.500   0.4773   0.00877   0.00206  -0.0877   0.5527   0.4286
  -1.000   0.5305   0.00845   0.00217  -0.0874   0.5248   0.6129
  -0.750   0.5559   0.00828   0.00225  -0.0869   0.5099   0.7125
  -0.500   0.5788   0.00808   0.00234  -0.0856   0.4953   0.8247
  -0.250   0.6082   0.00800   0.00243  -0.0855   0.4809   0.9540
   0.000   0.6461   0.00814   0.00248  -0.0878   0.4663   1.0001
   0.250   0.6727   0.00830   0.00256  -0.0876   0.4535   1.0001
   0.500   0.6992   0.00848   0.00265  -0.0874   0.4404   1.0001
   0.750   0.7257   0.00867   0.00275  -0.0872   0.4274   1.0001
   1.000   0.7525   0.00883   0.00285  -0.0871   0.4160   1.0001
   1.250   0.7792   0.00901   0.00297  -0.0870   0.4062   1.0001
   1.500   0.8056   0.00921   0.00309  -0.0868   0.3956   1.0001
   1.750   0.8319   0.00941   0.00323  -0.0866   0.3822   1.0001
   2.000   0.8576   0.00967   0.00339  -0.0864   0.3653   1.0001
   2.250   0.8834   0.00991   0.00355  -0.0862   0.3507   1.0001
   2.500   0.9096   0.01013   0.00371  -0.0860   0.3411   1.0001
   2.750   0.9358   0.01034   0.00388  -0.0859   0.3324   1.0001
   3.000   0.9621   0.01053   0.00405  -0.0858   0.3252   1.0001
   3.250   0.9881   0.01075   0.00423  -0.0857   0.3171   1.0001
   3.500   1.0142   0.01096   0.00442  -0.0855   0.3098   1.0001
   3.750   1.0401   0.01117   0.00462  -0.0854   0.3025   1.0001
   4.000   1.0657   0.01140   0.00483  -0.0852   0.2962   1.0001
   4.250   1.0916   0.01160   0.00503  -0.0851   0.2892   1.0001
   4.500   1.1167   0.01186   0.00528  -0.0848   0.2820   1.0001
   4.750   1.1423   0.01208   0.00550  -0.0847   0.2745   1.0001
   5.000   1.1668   0.01236   0.00575  -0.0844   0.2658   1.0001
   5.250   1.1914   0.01263   0.00602  -0.0841   0.2552   1.0001
   5.500   1.2155   0.01293   0.00630  -0.0838   0.2442   1.0001
   5.750   1.2389   0.01327   0.00660  -0.0833   0.2324   1.0001
   6.000   1.2615   0.01366   0.00693  -0.0828   0.2183   1.0001
   6.250   1.2826   0.01413   0.00733  -0.0820   0.1996   1.0001
   6.500   1.3016   0.01475   0.00782  -0.0809   0.1787   1.0001
   6.750   1.3207   0.01533   0.00832  -0.0799   0.1622   1.0001
   7.000   1.3396   0.01589   0.00882  -0.0788   0.1504   1.0001
   7.250   1.3590   0.01639   0.00931  -0.0778   0.1409   1.0001
   7.500   1.3771   0.01692   0.00982  -0.0766   0.1323   1.0001
   7.750   1.3930   0.01747   0.01036  -0.0750   0.1247   1.0001
   8.000   1.4096   0.01799   0.01088  -0.0736   0.1185   1.0001
   8.250   1.4243   0.01863   0.01151  -0.0719   0.1112   1.0001
   8.500   1.4404   0.01920   0.01210  -0.0706   0.1056   1.0001
   8.750   1.4551   0.01988   0.01278  -0.0691   0.0998   1.0001
   9.000   1.4699   0.02056   0.01348  -0.0677   0.0947   1.0001
   9.250   1.4841   0.02129   0.01424  -0.0663   0.0888   1.0001
   9.500   1.4970   0.02213   0.01508  -0.0648   0.0828   1.0001
   9.750   1.5079   0.02313   0.01606  -0.0632   0.0744   1.0001
  10.000   1.5172   0.02426   0.01716  -0.0616   0.0638   1.0001
  10.500   1.5127   0.02845   0.02112  -0.0567   0.0283   1.0001
  10.750   1.5158   0.03028   0.02300  -0.0551   0.0231   1.0001
  11.000   1.5206   0.03208   0.02484  -0.0538   0.0201   1.0001
  11.250   1.5258   0.03388   0.02671  -0.0527   0.0183   1.0001
  11.500   1.5303   0.03582   0.02872  -0.0518   0.0169   1.0001
  11.750   1.5334   0.03797   0.03093  -0.0509   0.0158   1.0001
  12.000   1.5378   0.04004   0.03310  -0.0503   0.0151   1.0001
  12.250   1.5406   0.04234   0.03549  -0.0497   0.0144   1.0001
  12.500   1.5418   0.04488   0.03812  -0.0492   0.0138   1.0001
  12.750   1.5412   0.04768   0.04101  -0.0489   0.0133   1.0001
  13.000   1.5387   0.05080   0.04422  -0.0487   0.0129   1.0001
  13.250   1.5371   0.05393   0.04746  -0.0487   0.0126   1.0001
  13.500   1.5355   0.05715   0.05079  -0.0488   0.0123   1.0001
  13.750   1.5323   0.06065   0.05441  -0.0491   0.0120   1.0001
  14.000   1.5278   0.06441   0.05828  -0.0496   0.0118   1.0001
  14.250   1.5224   0.06842   0.06240  -0.0502   0.0115   1.0001
  14.500   1.5155   0.07271   0.06680  -0.0510   0.0113   1.0001
  14.750   1.5072   0.07729   0.07151  -0.0519   0.0111   1.0001
  15.000   1.4979   0.08209   0.07642  -0.0531   0.0109   1.0001
  15.250   1.4874   0.08719   0.08163  -0.0544   0.0107   1.0001
  15.500   1.4757   0.09252   0.08708  -0.0558   0.0105   1.0001
  15.750   1.4628   0.09810   0.09278  -0.0575   0.0104   1.0001
  16.000   1.4490   0.10395   0.09875  -0.0593   0.0102   1.0001
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