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NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il)
Reynolds number: 500,000
Max Cl/Cd: 107.47 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n2h15-il-500000-n5.txt
Download as CSV file: xf-n2h15-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1152   0.08301   0.07914  -0.0927   0.6858   0.0267
 -10.000  -0.1193   0.07947   0.07563  -0.0942   0.6848   0.0268
  -9.750  -0.1230   0.07612   0.07230  -0.0954   0.6838   0.0268
  -9.500  -0.1298   0.07254   0.06876  -0.0968   0.6828   0.0268
  -9.250  -0.1442   0.06842   0.06465  -0.0992   0.6816   0.0268
  -9.000  -0.1577   0.06517   0.06140  -0.0995   0.6804   0.0268
  -8.750  -0.1721   0.06224   0.05845  -0.0981   0.6793   0.0268
  -8.500  -0.1831   0.05996   0.05614  -0.0956   0.6782   0.0267
  -8.000  -0.1882   0.05762   0.05381  -0.0900   0.6763   0.0254
  -7.750  -0.2075   0.05539   0.05153  -0.0851   0.6753   0.0251
  -7.500  -0.2254   0.05352   0.04959  -0.0798   0.6743   0.0253
  -7.250  -0.2443   0.05044   0.04642  -0.0745   0.6733   0.0240
  -7.000  -0.2533   0.04792   0.04381  -0.0701   0.6723   0.0240
  -6.750  -0.2666   0.04447   0.04021  -0.0646   0.6711   0.0236
  -6.500  -0.2729   0.04154   0.03711  -0.0597   0.6698   0.0235
  -6.250  -0.2765   0.03875   0.03413  -0.0548   0.6685   0.0235
  -6.000  -0.2702   0.03716   0.03244  -0.0516   0.6672   0.0238
  -5.750  -0.2626   0.03561   0.03076  -0.0484   0.6660   0.0241
  -5.500  -0.2637   0.03254   0.02741  -0.0431   0.6649   0.0238
  -5.250  -0.2593   0.03010   0.02472  -0.0387   0.6638   0.0239
  -5.000  -0.2516   0.02794   0.02231  -0.0348   0.6629   0.0239
  -4.750  -0.2404   0.02608   0.02019  -0.0315   0.6620   0.0240
  -4.500  -0.2255   0.02456   0.01845  -0.0289   0.6611   0.0242
  -4.250  -0.2087   0.02298   0.01663  -0.0266   0.6602   0.0243
  -4.000  -0.1887   0.02154   0.01494  -0.0250   0.6594   0.0245
  -3.750  -0.1657   0.02034   0.01352  -0.0240   0.6584   0.0247
  -3.500  -0.1402   0.01924   0.01226  -0.0236   0.6572   0.0249
  -3.250  -0.1122   0.01830   0.01117  -0.0237   0.6560   0.0254
  -3.000  -0.0814   0.01740   0.01013  -0.0244   0.6549   0.0256
  -2.750  -0.0473   0.01654   0.00915  -0.0259   0.6538   0.0258
  -2.500  -0.0118   0.01580   0.00830  -0.0277   0.6527   0.0262
  -2.250   0.0243   0.01518   0.00761  -0.0297   0.6516   0.0265
  -2.000   0.0626   0.01462   0.00699  -0.0321   0.6506   0.0267
  -1.750   0.1017   0.01406   0.00639  -0.0348   0.6496   0.0270
  -1.500   0.1416   0.01340   0.00573  -0.0377   0.6486   0.0274
  -1.250   0.1743   0.01302   0.00536  -0.0390   0.6475   0.0278
  -1.000   0.2053   0.01273   0.00508  -0.0398   0.6465   0.0283
  -0.750   0.2346   0.01251   0.00486  -0.0403   0.6456   0.0288
  -0.500   0.2639   0.01228   0.00463  -0.0408   0.6447   0.0294
  -0.250   0.2922   0.01212   0.00447  -0.0410   0.6438   0.0300
   0.000   0.3206   0.01196   0.00430  -0.0413   0.6429   0.0307
   0.250   0.3482   0.01186   0.00424  -0.0415   0.6418   0.0313
   0.500   0.3758   0.01179   0.00421  -0.0417   0.6404   0.0316
   0.750   0.4039   0.01168   0.00414  -0.0419   0.6390   0.0327
   1.000   0.4320   0.01160   0.00409  -0.0422   0.6374   0.0335
   1.250   0.4600   0.01155   0.00407  -0.0425   0.6361   0.0346
   1.500   0.4880   0.01152   0.00406  -0.0427   0.6348   0.0357
   1.750   0.5161   0.01149   0.00405  -0.0430   0.6337   0.0379
   2.000   0.5444   0.01145   0.00404  -0.0433   0.6325   0.0411
   2.250   0.5733   0.01139   0.00403  -0.0437   0.6314   0.0508
   2.750   0.7602   0.01095   0.00610  -0.0737   0.6302   0.9652
   3.250   0.8426   0.01147   0.00662  -0.0799   0.6284   0.9814
   3.500   0.8759   0.01152   0.00669  -0.0814   0.6272   0.9836
   3.750   0.9046   0.01171   0.00693  -0.0820   0.6244   0.9861
   4.000   0.9362   0.01170   0.00697  -0.0831   0.6207   0.9878
   4.250   0.9700   0.01159   0.00689  -0.0847   0.6183   0.9892
   4.500   1.0036   0.01138   0.00667  -0.0861   0.6146   0.9910
   4.750   1.0355   0.01132   0.00660  -0.0872   0.6125   0.9929
   5.250   1.1043   0.01099   0.00636  -0.0907   0.5964   0.9972
   5.500   1.1423   0.01075   0.00614  -0.0934   0.5787   0.9998
   5.750   1.1682   0.01087   0.00624  -0.0934   0.5618   1.0000
   6.000   1.1906   0.01123   0.00649  -0.0929   0.5314   1.0000
   6.250   1.2029   0.01285   0.00775  -0.0919   0.4614   1.0000
   6.500   1.1771   0.01771   0.01216  -0.0884   0.3733   1.0000
   6.750   1.1421   0.02000   0.01436  -0.0794   0.3520   1.0000
   7.000   1.1048   0.02300   0.01715  -0.0713   0.3094   1.0000
   7.250   1.0793   0.02582   0.01970  -0.0653   0.2621   1.0000
   7.500   1.0481   0.02928   0.02273  -0.0593   0.1836   1.0000
   7.750   1.0429   0.03134   0.02456  -0.0562   0.1411   1.0000
   8.000   1.0452   0.03299   0.02607  -0.0540   0.1132   1.0000
   8.250   1.0480   0.03466   0.02758  -0.0519   0.0834   1.0000
   8.500   1.0533   0.03619   0.02896  -0.0501   0.0605   1.0000
   8.750   1.0618   0.03753   0.03023  -0.0487   0.0491   1.0000
   9.000   1.0727   0.03870   0.03139  -0.0475   0.0430   1.0000
   9.250   1.0848   0.03981   0.03249  -0.0464   0.0394   1.0000
   9.500   1.0973   0.04089   0.03357  -0.0453   0.0366   1.0000
   9.750   1.1089   0.04207   0.03475  -0.0443   0.0342   1.0000
  10.000   1.1210   0.04323   0.03593  -0.0432   0.0324   1.0000
  10.250   1.1337   0.04433   0.03707  -0.0423   0.0308   1.0000
  10.500   1.1457   0.04550   0.03825  -0.0413   0.0295   1.0000
  10.750   1.1568   0.04677   0.03953  -0.0404   0.0283   1.0000
  11.000   1.1684   0.04803   0.04082  -0.0394   0.0271   1.0000
  11.250   1.1804   0.04925   0.04209  -0.0386   0.0263   1.0000
  11.500   1.1921   0.05050   0.04338  -0.0377   0.0252   1.0000
  11.750   1.2035   0.05177   0.04467  -0.0369   0.0242   1.0000
  12.000   1.2131   0.05326   0.04617  -0.0359   0.0230   1.0000
  12.250   1.2232   0.05470   0.04764  -0.0351   0.0225   1.0000
  12.500   1.2350   0.05599   0.04899  -0.0344   0.0218   1.0000
  12.750   1.2462   0.05734   0.05039  -0.0336   0.0210   1.0000
  13.000   1.2567   0.05879   0.05188  -0.0329   0.0202   1.0000
  13.250   1.2669   0.06026   0.05338  -0.0322   0.0195   1.0000
  13.500   1.2753   0.06191   0.05506  -0.0314   0.0189   1.0000
  13.750   1.2841   0.06355   0.05673  -0.0307   0.0184   1.0000
  14.000   1.2929   0.06521   0.05846  -0.0300   0.0181   1.0000
  14.250   1.3023   0.06684   0.06015  -0.0293   0.0175   1.0000
  14.500   1.3118   0.06845   0.06182  -0.0288   0.0169   1.0000
  14.750   1.3217   0.07001   0.06343  -0.0282   0.0164   1.0000
  15.000   1.3298   0.07179   0.06526  -0.0277   0.0159   1.0000
  15.250   1.3373   0.07365   0.06716  -0.0272   0.0155   1.0000
  15.500   1.3441   0.07560   0.06915  -0.0266   0.0151   1.0000
  15.750   1.3493   0.07776   0.07136  -0.0261   0.0148   1.0000
  16.000   1.3554   0.07983   0.07351  -0.0256   0.0146   1.0000
  16.250   1.3630   0.08174   0.07551  -0.0252   0.0143   1.0000
  16.500   1.3694   0.08377   0.07762  -0.0248   0.0140   1.0000
  16.750   1.3750   0.08597   0.07990  -0.0245   0.0137   1.0000
  17.000   1.3814   0.08807   0.08207  -0.0242   0.0133   1.0000
  17.250   1.3855   0.09046   0.08454  -0.0239   0.0132   1.0000
  17.500   1.3903   0.09281   0.08696  -0.0238   0.0129   1.0000
  17.750   1.3945   0.09523   0.08946  -0.0237   0.0127   1.0000
  18.000   1.3986   0.09773   0.09202  -0.0237   0.0123   1.0000
  18.250   1.4020   0.10031   0.09466  -0.0238   0.0121   1.0000
  18.500   1.4025   0.10328   0.09770  -0.0238   0.0119   1.0000
  18.750   1.4021   0.10641   0.10090  -0.0239   0.0117   1.0000
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