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N-22 (n22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.47 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n22-il-1000000.txt
Download as CSV file: xf-n22-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -1.0023   0.04268   0.04002  -0.0881   0.9999   0.0206
 -16.250  -1.0277   0.03461   0.03167  -0.0977   0.9999   0.0207
 -16.000  -1.0333   0.03213   0.02907  -0.0970   0.9999   0.0209
 -15.750  -1.0240   0.03078   0.02766  -0.0961   0.9999   0.0212
 -15.500  -1.0117   0.02992   0.02676  -0.0948   0.9999   0.0214
 -15.250  -0.9997   0.02928   0.02610  -0.0929   0.9999   0.0217
 -15.000  -0.9901   0.02865   0.02543  -0.0905   0.9999   0.0220
 -14.750  -0.9824   0.02800   0.02473  -0.0878   0.9999   0.0222
 -14.500  -0.9652   0.02717   0.02381  -0.0868   0.9993   0.0226
 -14.250  -0.9372   0.02607   0.02259  -0.0881   0.9977   0.0231
 -14.000  -0.9085   0.02500   0.02139  -0.0893   0.9961   0.0235
 -13.750  -0.8782   0.02412   0.02038  -0.0905   0.9947   0.0239
 -13.500  -0.8461   0.02355   0.01970  -0.0918   0.9936   0.0241
 -13.250  -0.8250   0.02114   0.01709  -0.0926   0.9906   0.0249
 -13.000  -0.7939   0.02061   0.01655  -0.0936   0.9887   0.0254
 -12.750  -0.7617   0.02009   0.01600  -0.0947   0.9871   0.0258
 -12.500  -0.7297   0.01947   0.01531  -0.0959   0.9854   0.0263
 -12.250  -0.6981   0.01881   0.01457  -0.0969   0.9834   0.0268
 -12.000  -0.6691   0.01826   0.01393  -0.0973   0.9799   0.0274
 -11.750  -0.6414   0.01777   0.01335  -0.0973   0.9751   0.0279
 -11.500  -0.6132   0.01732   0.01281  -0.0973   0.9709   0.0282
 -11.250  -0.5882   0.01676   0.01215  -0.0968   0.9650   0.0285
 -11.000  -0.5676   0.01533   0.01059  -0.0958   0.9581   0.0293
 -10.750  -0.5428   0.01487   0.01010  -0.0951   0.9520   0.0299
 -10.500  -0.5178   0.01452   0.00971  -0.0943   0.9448   0.0304
 -10.250  -0.4926   0.01413   0.00926  -0.0936   0.9384   0.0309
 -10.000  -0.4670   0.01370   0.00878  -0.0930   0.9306   0.0314
  -9.750  -0.4415   0.01330   0.00829  -0.0923   0.9235   0.0319
  -9.500  -0.4150   0.01293   0.00785  -0.0918   0.9151   0.0325
  -9.250  -0.3886   0.01265   0.00749  -0.0912   0.9072   0.0330
  -9.000  -0.3614   0.01238   0.00716  -0.0909   0.8980   0.0333
  -8.750  -0.3362   0.01162   0.00630  -0.0903   0.8889   0.0341
  -8.500  -0.3098   0.01113   0.00575  -0.0899   0.8788   0.0348
  -8.250  -0.2826   0.01082   0.00540  -0.0895   0.8687   0.0355
  -8.000  -0.2554   0.01058   0.00509  -0.0892   0.8582   0.0362
  -7.750  -0.2276   0.01035   0.00481  -0.0889   0.8469   0.0370
  -7.500  -0.1998   0.01015   0.00454  -0.0886   0.8357   0.0379
  -7.250  -0.1721   0.00996   0.00427  -0.0884   0.8243   0.0386
  -7.000  -0.1441   0.00980   0.00404  -0.0881   0.8120   0.0391
  -6.750  -0.1168   0.00939   0.00356  -0.0879   0.7992   0.0405
  -6.500  -0.0889   0.00919   0.00330  -0.0877   0.7871   0.0418
  -6.250  -0.0607   0.00905   0.00311  -0.0875   0.7762   0.0431
  -6.000  -0.0323   0.00892   0.00293  -0.0875   0.7660   0.0446
  -5.750  -0.0037   0.00883   0.00279  -0.0874   0.7567   0.0457
  -5.500   0.0245   0.00859   0.00251  -0.0873   0.7473   0.0489
  -5.250   0.0531   0.00846   0.00237  -0.0873   0.7384   0.0516
  -4.750   0.1102   0.00820   0.00206  -0.0872   0.7203   0.0601
  -4.500   0.1387   0.00809   0.00193  -0.0872   0.7118   0.0674
  -4.250   0.1674   0.00794   0.00184  -0.0873   0.7031   0.0803
  -4.000   0.1959   0.00784   0.00176  -0.0873   0.6941   0.0990
  -3.750   0.2245   0.00773   0.00170  -0.0873   0.6847   0.1168
  -3.500   0.2532   0.00767   0.00165  -0.0874   0.6761   0.1323
  -3.250   0.2819   0.00760   0.00161  -0.0875   0.6668   0.1482
  -3.000   0.3105   0.00753   0.00157  -0.0876   0.6574   0.1671
  -2.750   0.3389   0.00748   0.00154  -0.0876   0.6469   0.1911
  -2.500   0.3675   0.00737   0.00152  -0.0877   0.6360   0.2249
  -2.250   0.3957   0.00724   0.00150  -0.0878   0.6256   0.2761
  -2.000   0.4236   0.00707   0.00151  -0.0879   0.6143   0.3493
  -1.750   0.4516   0.00685   0.00153  -0.0881   0.6026   0.4408
  -1.500   0.4789   0.00660   0.00156  -0.0881   0.5900   0.5572
  -1.250   0.5051   0.00629   0.00163  -0.0878   0.5767   0.7015
  -1.000   0.5270   0.00591   0.00172  -0.0863   0.5629   0.8705
  -0.750   0.5587   0.00585   0.00176  -0.0868   0.5482   0.9797
  -0.500   0.5983   0.00597   0.00179  -0.0894   0.5322   1.0001
  -0.250   0.6251   0.00610   0.00184  -0.0892   0.5169   1.0001
   0.000   0.6519   0.00625   0.00189  -0.0890   0.5008   1.0001
   0.250   0.6787   0.00640   0.00195  -0.0888   0.4844   1.0001
   0.500   0.7057   0.00656   0.00203  -0.0887   0.4688   1.0001
   0.750   0.7327   0.00673   0.00211  -0.0886   0.4538   1.0001
   1.000   0.7594   0.00692   0.00221  -0.0884   0.4365   1.0001
   1.250   0.7860   0.00713   0.00231  -0.0883   0.4161   1.0001
   1.500   0.8126   0.00734   0.00242  -0.0882   0.3976   1.0001
   1.750   0.8395   0.00753   0.00254  -0.0881   0.3844   1.0001
   2.250   0.8937   0.00786   0.00277  -0.0881   0.3639   1.0001
   2.500   0.9206   0.00805   0.00291  -0.0880   0.3545   1.0001
   2.750   0.9476   0.00821   0.00304  -0.0880   0.3455   1.0001
   3.000   0.9746   0.00839   0.00317  -0.0880   0.3380   1.0001
   3.250   1.0016   0.00855   0.00331  -0.0881   0.3307   1.0001
   3.500   1.0283   0.00874   0.00347  -0.0880   0.3236   1.0001
   3.750   1.0554   0.00889   0.00361  -0.0881   0.3172   1.0001
   4.250   1.1086   0.00925   0.00394  -0.0881   0.3029   1.0001
   4.500   1.1346   0.00948   0.00413  -0.0880   0.2949   1.0001
   4.750   1.1613   0.00964   0.00430  -0.0880   0.2884   1.0001
   5.000   1.1871   0.00986   0.00449  -0.0879   0.2804   1.0001
   5.250   1.2131   0.01007   0.00468  -0.0879   0.2713   1.0001
   5.500   1.2382   0.01034   0.00491  -0.0877   0.2593   1.0001
   5.750   1.2628   0.01064   0.00515  -0.0874   0.2452   1.0001
   6.000   1.2868   0.01098   0.00541  -0.0871   0.2287   1.0001
   6.250   1.3095   0.01140   0.00574  -0.0866   0.2083   1.0001
   6.500   1.3307   0.01193   0.00614  -0.0858   0.1859   1.0001
   6.750   1.3515   0.01246   0.00656  -0.0850   0.1665   1.0001
   7.000   1.3719   0.01300   0.00701  -0.0842   0.1506   1.0001
   7.250   1.3932   0.01345   0.00741  -0.0834   0.1398   1.0001
   7.500   1.4141   0.01391   0.00783  -0.0827   0.1305   1.0001
   7.750   1.4348   0.01436   0.00825  -0.0819   0.1226   1.0001
   8.000   1.4555   0.01478   0.00865  -0.0811   0.1158   1.0001
   8.250   1.4744   0.01527   0.00912  -0.0800   0.1086   1.0001
   8.500   1.4942   0.01567   0.00953  -0.0791   0.1037   1.0001
   8.750   1.5100   0.01618   0.01001  -0.0775   0.0971   1.0001
   9.000   1.5266   0.01666   0.01049  -0.0760   0.0913   1.0001
   9.250   1.5404   0.01731   0.01111  -0.0742   0.0833   1.0001
   9.500   1.5535   0.01802   0.01177  -0.0724   0.0736   1.0001
   9.750   1.5591   0.01920   0.01282  -0.0697   0.0541   1.0001
  10.000   1.5524   0.02121   0.01464  -0.0656   0.0293   1.0001
  10.250   1.5572   0.02259   0.01600  -0.0632   0.0229   1.0001
  10.500   1.5644   0.02387   0.01732  -0.0613   0.0200   1.0001
  10.750   1.5746   0.02499   0.01848  -0.0599   0.0187   1.0001
  11.000   1.5826   0.02632   0.01986  -0.0584   0.0175   1.0001
  11.250   1.5880   0.02790   0.02150  -0.0568   0.0164   1.0001
  11.500   1.5974   0.02923   0.02289  -0.0558   0.0159   1.0001
  11.750   1.6051   0.03074   0.02448  -0.0547   0.0153   1.0001
  12.000   1.6113   0.03244   0.02624  -0.0537   0.0148   1.0001
  12.250   1.6150   0.03442   0.02828  -0.0527   0.0142   1.0001
  12.500   1.6148   0.03687   0.03081  -0.0517   0.0137   1.0001
  12.750   1.6171   0.03914   0.03317  -0.0509   0.0133   1.0001
  13.000   1.6207   0.04133   0.03545  -0.0504   0.0131   1.0001
  13.250   1.6227   0.04377   0.03797  -0.0500   0.0128   1.0001
  13.500   1.6231   0.04647   0.04076  -0.0497   0.0125   1.0001
  13.750   1.6223   0.04936   0.04374  -0.0495   0.0123   1.0001
  14.000   1.6202   0.05251   0.04698  -0.0495   0.0120   1.0001
  14.250   1.6162   0.05601   0.05057  -0.0496   0.0118   1.0001
  14.500   1.6100   0.05988   0.05454  -0.0499   0.0116   1.0001
  14.750   1.6009   0.06423   0.05899  -0.0504   0.0114   1.0001
  15.000   1.5892   0.06908   0.06395  -0.0512   0.0112   1.0001
  15.250   1.5737   0.07462   0.06962  -0.0523   0.0111   1.0001
  15.500   1.5564   0.08052   0.07564  -0.0536   0.0109   1.0001
  15.750   1.5440   0.08583   0.08107  -0.0549   0.0109   1.0001
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