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NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.21 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n1h15-il-1000000.txt
Download as CSV file: xf-n1h15-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1-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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2687   0.09497   0.09232  -0.0483   0.7034   0.0211
 -10.000  -0.2677   0.09111   0.08846  -0.0503   0.7024   0.0211
  -9.750  -0.2773   0.08546   0.08283  -0.0527   0.7015   0.0213
  -9.500  -0.2703   0.08334   0.08070  -0.0532   0.7006   0.0215
  -9.250  -0.2653   0.08089   0.07826  -0.0542   0.6997   0.0216
  -9.000  -0.2646   0.07793   0.07530  -0.0557   0.6986   0.0217
  -8.750  -0.2660   0.07501   0.07239  -0.0572   0.6973   0.0219
  -8.500  -0.2740   0.07186   0.06925  -0.0591   0.6960   0.0221
  -8.250  -0.2816   0.06908   0.06649  -0.0594   0.6951   0.0223
  -8.000  -0.2880   0.06591   0.06331  -0.0599   0.6941   0.0225
  -7.750  -0.2874   0.06266   0.06004  -0.0608   0.6930   0.0229
  -7.500  -0.2860   0.05899   0.05632  -0.0617   0.6918   0.0234
  -7.000  -0.3124   0.04082   0.03751  -0.0607   0.6896   0.0256
  -6.750  -0.2975   0.03919   0.03581  -0.0601   0.6885   0.0258
  -6.500  -0.2805   0.03790   0.03446  -0.0595   0.6876   0.0261
  -6.250  -0.2623   0.03665   0.03314  -0.0591   0.6866   0.0263
  -6.000  -0.2449   0.03496   0.03134  -0.0583   0.6857   0.0267
  -5.750  -0.2273   0.03308   0.02933  -0.0575   0.6847   0.0273
  -5.500  -0.2101   0.03079   0.02685  -0.0563   0.6836   0.0284
  -5.250  -0.1928   0.02831   0.02381  -0.0535   0.6822   0.0301
  -5.000  -0.1861   0.02340   0.01858  -0.0510   0.6811   0.0310
  -4.750  -0.1620   0.02253   0.01770  -0.0508   0.6803   0.0314
  -4.500  -0.1378   0.02177   0.01689  -0.0506   0.6794   0.0319
  -4.250  -0.1137   0.02092   0.01596  -0.0502   0.6784   0.0328
  -4.000  -0.0892   0.01996   0.01483  -0.0496   0.6774   0.0344
  -3.750  -0.0687   0.01627   0.01055  -0.0474   0.6764   0.0294
  -3.500  -0.0427   0.01502   0.00915  -0.0471   0.6754   0.0291
  -3.250  -0.0156   0.01415   0.00816  -0.0470   0.6744   0.0290
  -3.000   0.0120   0.01369   0.00762  -0.0470   0.6733   0.0295
  -2.750   0.0398   0.01316   0.00702  -0.0471   0.6722   0.0297
  -2.500   0.0676   0.01276   0.00655  -0.0471   0.6712   0.0299
  -2.250   0.0955   0.01248   0.00621  -0.0472   0.6702   0.0302
  -2.000   0.1229   0.01182   0.00552  -0.0473   0.6693   0.0304
  -1.750   0.1492   0.01123   0.00491  -0.0471   0.6681   0.0307
  -1.500   0.1756   0.01092   0.00459  -0.0470   0.6668   0.0310
  -1.250   0.2026   0.01061   0.00430  -0.0470   0.6661   0.0314
  -1.000   0.2298   0.01037   0.00409  -0.0470   0.6651   0.0319
  -0.750   0.2571   0.01018   0.00391  -0.0471   0.6640   0.0325
  -0.500   0.2848   0.01003   0.00379  -0.0472   0.6628   0.0335
  -0.250   0.3123   0.00988   0.00364  -0.0473   0.6616   0.0342
   0.000   0.3399   0.00976   0.00352  -0.0474   0.6605   0.0350
   0.250   0.3677   0.00965   0.00342  -0.0476   0.6594   0.0357
   0.500   0.3952   0.00952   0.00328  -0.0477   0.6584   0.0366
   0.750   0.4228   0.00939   0.00316  -0.0477   0.6573   0.0384
   1.000   0.4506   0.00931   0.00308  -0.0479   0.6563   0.0405
   1.250   0.4785   0.00925   0.00302  -0.0481   0.6552   0.0434
   1.500   0.5048   0.00907   0.00301  -0.0479   0.6540   0.0991
   1.750   0.5011   0.00731   0.00308  -0.0421   0.6523   0.7503
   2.000   0.6506   0.00765   0.00399  -0.0681   0.6523   0.9799
   2.250   0.7124   0.00784   0.00418  -0.0756   0.6518   0.9865
   2.500   0.7611   0.00790   0.00424  -0.0804   0.6510   0.9911
   2.750   0.8146   0.00784   0.00419  -0.0862   0.6498   0.9961
   3.000   0.8562   0.00763   0.00400  -0.0894   0.6465   0.9988
   3.250   0.8891   0.00756   0.00393  -0.0908   0.6446   0.9998
   3.500   0.9170   0.00753   0.00390  -0.0912   0.6429   1.0000
   3.750   0.9432   0.00749   0.00384  -0.0911   0.6406   1.0000
   4.000   0.9689   0.00751   0.00383  -0.0909   0.6377   1.0000
   4.250   0.9963   0.00753   0.00390  -0.0913   0.6355   1.0000
   4.500   1.0236   0.00753   0.00395  -0.0916   0.6322   1.0000
   4.750   1.0508   0.00749   0.00392  -0.0918   0.6282   1.0000
   5.000   1.0773   0.00745   0.00385  -0.0918   0.6227   1.0000
   5.250   1.1066   0.00750   0.00397  -0.0927   0.6148   1.0000
   5.500   1.1350   0.00758   0.00404  -0.0933   0.6056   1.0000
   5.750   1.1641   0.00775   0.00420  -0.0942   0.5940   1.0000
   6.000   1.1956   0.00814   0.00459  -0.0960   0.5751   1.0000
   6.250   1.2301   0.01000   0.00618  -0.1008   0.5095   1.0000
   6.500   1.2101   0.01415   0.00987  -0.0981   0.4209   1.0000
   6.750   1.1763   0.01555   0.01120  -0.0883   0.4047   1.0000
   7.000   1.1421   0.01727   0.01280  -0.0789   0.3787   1.0000
   7.250   1.1119   0.01945   0.01477  -0.0711   0.3386   1.0000
   7.500   1.0769   0.02227   0.01725  -0.0633   0.2762   1.0000
   7.750   1.0494   0.02501   0.01961  -0.0569   0.2073   1.0000
   8.000   1.0327   0.02737   0.02164  -0.0521   0.1456   1.0000
   8.250   1.0242   0.02940   0.02340  -0.0484   0.0968   1.0000
   8.500   1.0220   0.03113   0.02490  -0.0455   0.0584   1.0000
   8.750   1.0303   0.03224   0.02595  -0.0437   0.0478   1.0000
   9.000   1.0409   0.03324   0.02693  -0.0422   0.0441   1.0000
   9.250   1.0519   0.03422   0.02791  -0.0408   0.0410   1.0000
   9.500   1.0651   0.03507   0.02878  -0.0395   0.0397   1.0000
   9.750   1.0779   0.03596   0.02967  -0.0383   0.0381   1.0000
  10.000   1.0887   0.03700   0.03074  -0.0370   0.0368   1.0000
  10.250   1.0986   0.03813   0.03187  -0.0356   0.0353   1.0000
  10.500   1.1089   0.03924   0.03301  -0.0342   0.0342   1.0000
  10.750   1.1224   0.04013   0.03393  -0.0332   0.0336   1.0000
  11.000   1.1349   0.04112   0.03494  -0.0321   0.0329   1.0000
  11.250   1.1466   0.04218   0.03603  -0.0311   0.0320   1.0000
  11.500   1.1581   0.04325   0.03713  -0.0300   0.0313   1.0000
  11.750   1.1689   0.04439   0.03828  -0.0289   0.0303   1.0000
  12.000   1.1780   0.04569   0.03959  -0.0277   0.0294   1.0000
  12.250   1.1819   0.04746   0.04141  -0.0261   0.0283   1.0000
  12.500   1.1955   0.04843   0.04242  -0.0254   0.0279   1.0000
  12.750   1.2076   0.04952   0.04355  -0.0245   0.0274   1.0000
  13.000   1.2193   0.05066   0.04472  -0.0236   0.0269   1.0000
  13.250   1.2303   0.05189   0.04598  -0.0228   0.0262   1.0000
  13.500   1.2407   0.05317   0.04729  -0.0219   0.0256   1.0000
  13.750   1.2525   0.05434   0.04847  -0.0212   0.0248   1.0000
  14.000   1.2605   0.05585   0.05001  -0.0202   0.0243   1.0000
  14.250   1.2604   0.05807   0.05227  -0.0187   0.0233   1.0000
  14.500   1.2727   0.05925   0.05350  -0.0181   0.0230   1.0000
  14.750   1.2845   0.06047   0.05476  -0.0176   0.0225   1.0000
  15.000   1.2960   0.06172   0.05606  -0.0170   0.0220   1.0000
  15.250   1.3064   0.06310   0.05748  -0.0164   0.0214   1.0000
  15.500   1.3177   0.06442   0.05882  -0.0159   0.0208   1.0000
  15.750   1.3258   0.06603   0.06047  -0.0152   0.0203   1.0000
  16.000   1.3355   0.06748   0.06193  -0.0147   0.0198   1.0000
  16.250   1.3340   0.07000   0.06450  -0.0136   0.0190   1.0000
  16.500   1.3435   0.07153   0.06609  -0.0131   0.0188   1.0000
  16.750   1.3540   0.07298   0.06760  -0.0127   0.0184   1.0000
  17.000   1.3622   0.07465   0.06932  -0.0123   0.0181   1.0000
  17.250   1.3699   0.07642   0.07115  -0.0119   0.0176   1.0000
  17.500   1.3793   0.07801   0.07278  -0.0117   0.0171   1.0000
  17.750   1.3861   0.07985   0.07467  -0.0113   0.0168   1.0000
  18.000   1.3936   0.08169   0.07653  -0.0111   0.0163   1.0000
  18.250   1.3975   0.08390   0.07878  -0.0107   0.0159   1.0000
  18.500   1.3957   0.08671   0.08165  -0.0102   0.0154   1.0000
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