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NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.08 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n2h15-il-1000000-n5.txt
Download as CSV file: xf-n2h15-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2-H-15 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1295   0.08500   0.08177  -0.0884   0.6719   0.0168
 -10.500  -0.1279   0.08187   0.07866  -0.0900   0.6712   0.0170
 -10.250  -0.1258   0.07893   0.07573  -0.0914   0.6704   0.0174
 -10.000  -0.1304   0.07498   0.07180  -0.0934   0.6696   0.0178
  -9.750  -0.1383   0.07082   0.06766  -0.0954   0.6687   0.0179
  -9.500  -0.1527   0.06612   0.06299  -0.0981   0.6676   0.0180
  -9.250  -0.1834   0.06064   0.05751  -0.1011   0.6664   0.0182
  -9.000  -0.2049   0.05729   0.05414  -0.0996   0.6652   0.0181
  -8.750  -0.2311   0.05406   0.05087  -0.0958   0.6642   0.0181
  -8.500  -0.2577   0.05122   0.04798  -0.0903   0.6630   0.0181
  -8.250  -0.2916   0.04818   0.04485  -0.0825   0.6619   0.0183
  -8.000  -0.3151   0.04499   0.04155  -0.0760   0.6608   0.0184
  -7.750  -0.3509   0.03950   0.03581  -0.0672   0.6597   0.0186
  -7.500  -0.3893   0.03318   0.02911  -0.0571   0.6585   0.0190
  -7.250  -0.3954   0.03052   0.02626  -0.0516   0.6577   0.0191
  -7.000  -0.3878   0.02928   0.02491  -0.0482   0.6569   0.0192
  -6.750  -0.3799   0.02791   0.02342  -0.0448   0.6559   0.0193
  -6.500  -0.3743   0.02606   0.02139  -0.0409   0.6549   0.0195
  -6.250  -0.3567   0.02579   0.02108  -0.0392   0.6538   0.0196
  -6.000  -0.3484   0.02395   0.01905  -0.0355   0.6528   0.0198
  -5.750  -0.3358   0.02250   0.01742  -0.0326   0.6518   0.0199
  -5.500  -0.3235   0.02053   0.01520  -0.0296   0.6508   0.0201
  -5.250  -0.3060   0.01908   0.01354  -0.0276   0.6498   0.0203
  -5.000  -0.2848   0.01762   0.01185  -0.0264   0.6489   0.0205
  -4.750  -0.2593   0.01635   0.01038  -0.0260   0.6479   0.0207
  -4.500  -0.2316   0.01544   0.00933  -0.0261   0.6469   0.0208
  -4.250  -0.2005   0.01453   0.00828  -0.0270   0.6459   0.0211
  -4.000  -0.1688   0.01385   0.00748  -0.0280   0.6448   0.0214
  -3.750  -0.1376   0.01334   0.00689  -0.0289   0.6435   0.0217
  -3.500  -0.0984   0.01264   0.00612  -0.0315   0.6426   0.0219
  -3.250  -0.0624   0.01215   0.00558  -0.0335   0.6419   0.0222
  -3.000  -0.0281   0.01173   0.00513  -0.0351   0.6411   0.0223
  -2.750   0.0034   0.01142   0.00480  -0.0360   0.6402   0.0224
  -2.500   0.0392   0.01093   0.00428  -0.0380   0.6393   0.0228
  -2.250   0.0710   0.01060   0.00396  -0.0390   0.6383   0.0230
  -2.000   0.1008   0.01035   0.00371  -0.0396   0.6372   0.0233
  -1.750   0.1294   0.01016   0.00353  -0.0399   0.6360   0.0236
  -1.500   0.1578   0.00997   0.00335  -0.0402   0.6348   0.0238
  -1.250   0.1860   0.00981   0.00319  -0.0404   0.6336   0.0241
  -1.000   0.2142   0.00965   0.00302  -0.0406   0.6325   0.0244
  -0.750   0.2421   0.00951   0.00289  -0.0407   0.6315   0.0247
  -0.500   0.2703   0.00936   0.00273  -0.0409   0.6304   0.0251
  -0.250   0.2983   0.00924   0.00261  -0.0411   0.6293   0.0253
   0.000   0.3260   0.00917   0.00254  -0.0412   0.6281   0.0259
   0.250   0.3542   0.00908   0.00247  -0.0414   0.6271   0.0264
   0.500   0.3824   0.00899   0.00241  -0.0416   0.6261   0.0267
   0.750   0.4114   0.00887   0.00231  -0.0420   0.6249   0.0277
   1.000   0.4403   0.00879   0.00226  -0.0424   0.6237   0.0282
   1.250   0.4690   0.00873   0.00223  -0.0428   0.6226   0.0289
   1.500   0.4976   0.00868   0.00222  -0.0431   0.6213   0.0295
   1.750   0.5263   0.00864   0.00220  -0.0435   0.6201   0.0307
   2.000   0.5547   0.00861   0.00219  -0.0438   0.6187   0.0313
   2.250   0.5832   0.00858   0.00218  -0.0441   0.6173   0.0335
   2.500   0.6117   0.00855   0.00219  -0.0444   0.6161   0.0374
   2.750   0.6735   0.00690   0.00261  -0.0533   0.6152   0.8170
   3.000   0.7067   0.00688   0.00270  -0.0546   0.6139   0.8570
   3.500   0.8514   0.00749   0.00358  -0.0750   0.6097   0.9036
   3.750   0.9146   0.00786   0.00401  -0.0830   0.6059   0.9144
   4.000   0.9504   0.00797   0.00414  -0.0849   0.6025   0.9173
   4.250   0.9876   0.00809   0.00426  -0.0871   0.5991   0.9227
   5.250   1.0375   0.00908   0.00518  -0.0746   0.5596   0.9736
   5.500   1.0648   0.00955   0.00550  -0.0752   0.5246   0.9749
   5.750   1.0769   0.01156   0.00707  -0.0743   0.4303   0.9774
   6.000   1.0637   0.01683   0.01174  -0.0739   0.3025   0.9818
   6.500   1.0101   0.02291   0.01727  -0.0627   0.1849   0.9920
   7.000   1.0109   0.02641   0.02043  -0.0580   0.1133   0.9956
   7.250   1.0208   0.02765   0.02153  -0.0571   0.0872   0.9963
   7.500   1.0286   0.02902   0.02278  -0.0557   0.0630   0.9969
   7.750   1.0391   0.03017   0.02384  -0.0545   0.0478   0.9973
   8.000   1.0517   0.03116   0.02479  -0.0534   0.0399   0.9975
   8.250   1.0663   0.03208   0.02570  -0.0526   0.0365   0.9978
   8.500   1.0812   0.03303   0.02663  -0.0519   0.0334   0.9982
   8.750   1.0960   0.03388   0.02749  -0.0510   0.0314   0.9983
   9.000   1.1095   0.03480   0.02841  -0.0499   0.0296   0.9983
   9.250   1.1220   0.03577   0.02938  -0.0486   0.0279   0.9982
   9.500   1.1347   0.03674   0.03037  -0.0474   0.0270   0.9981
   9.750   1.1476   0.03768   0.03132  -0.0462   0.0262   0.9979
  10.000   1.1597   0.03867   0.03233  -0.0449   0.0250   0.9977
  10.250   1.1717   0.03967   0.03333  -0.0436   0.0239   0.9974
  10.500   1.1832   0.04074   0.03441  -0.0424   0.0229   0.9973
  10.750   1.1965   0.04176   0.03545  -0.0414   0.0221   0.9972
  11.000   1.2089   0.04281   0.03652  -0.0404   0.0211   0.9971
  11.250   1.2213   0.04384   0.03756  -0.0393   0.0204   0.9970
  11.500   1.2332   0.04494   0.03867  -0.0382   0.0195   0.9969
  11.750   1.2432   0.04613   0.03987  -0.0369   0.0186   0.9967
  12.000   1.2528   0.04732   0.04109  -0.0354   0.0180   0.9963
  12.250   1.2638   0.04847   0.04226  -0.0342   0.0176   0.9962
  12.500   1.2745   0.04963   0.04346  -0.0329   0.0172   0.9960
  12.750   1.2841   0.05082   0.04467  -0.0315   0.0166   0.9957
  13.000   1.2917   0.05218   0.04605  -0.0298   0.0159   0.9955
  13.250   1.3017   0.05352   0.04740  -0.0288   0.0153   0.9954
  13.500   1.3116   0.05488   0.04879  -0.0278   0.0147   0.9954
  13.750   1.3228   0.05611   0.05005  -0.0269   0.0143   0.9953
  14.000   1.3322   0.05751   0.05150  -0.0258   0.0141   0.9953
  14.250   1.3404   0.05902   0.05304  -0.0246   0.0137   0.9951
  14.500   1.3472   0.06064   0.05469  -0.0230   0.0133   0.9950
  15.500   1.3787   0.06761   0.06178  -0.0190   0.0117   0.9946
  15.750   1.3885   0.06908   0.06330  -0.0185   0.0116   0.9946
  16.000   1.3968   0.07072   0.06499  -0.0179   0.0114   0.9946
  16.250   1.4054   0.07235   0.06668  -0.0175   0.0112   0.9946
  16.500   1.4147   0.07390   0.06827  -0.0171   0.0109   0.9946
  16.750   1.4221   0.07566   0.07008  -0.0166   0.0106   0.9946
  17.000   1.4296   0.07744   0.07192  -0.0162   0.0104   0.9946
  17.250   1.4357   0.07939   0.07393  -0.0158   0.0103   0.9945
  17.500   1.4429   0.08120   0.07578  -0.0154   0.0101   0.9945
  17.750   1.4479   0.08333   0.07797  -0.0151   0.0099   0.9945
  18.000   1.4534   0.08540   0.08008  -0.0148   0.0096   0.9945
  18.250   1.4589   0.08747   0.08221  -0.0146   0.0095   0.9945
  18.500   1.4608   0.09001   0.08481  -0.0143   0.0093   0.9945
  18.750   1.4627   0.09257   0.08743  -0.0141   0.0090   0.9944
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