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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 500,000
Max Cl/Cd: 70.02 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n5h10-il-500000.txt
Download as CSV file: xf-n5h10-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 5-H-10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5076   0.08715   0.08462  -0.0204   0.8411   0.0188
  -9.000  -0.5156   0.08211   0.07959  -0.0243   0.8356   0.0188
  -8.750  -0.5264   0.07765   0.07507  -0.0259   0.8303   0.0188
  -8.500  -0.5362   0.07393   0.07130  -0.0255   0.8251   0.0188
  -8.250  -0.5549   0.06763   0.06492  -0.0254   0.8202   0.0190
  -8.000  -0.5632   0.06318   0.06038  -0.0246   0.8159   0.0194
  -7.750  -0.5606   0.06011   0.05724  -0.0239   0.8115   0.0197
  -7.500  -0.5538   0.05768   0.05474  -0.0233   0.8068   0.0201
  -7.250  -0.5455   0.05522   0.05218  -0.0225   0.8026   0.0207
  -7.000  -0.5361   0.05248   0.04931  -0.0218   0.7985   0.0217
  -6.750  -0.5265   0.04884   0.04551  -0.0208   0.7937   0.0228
  -6.500  -0.5067   0.04597   0.04226  -0.0190   0.7894   0.0254
  -6.250  -0.4955   0.04266   0.03864  -0.0170   0.7855   0.0255
  -6.000  -0.4841   0.03901   0.03469  -0.0150   0.7806   0.0256
  -5.750  -0.4709   0.03556   0.03092  -0.0130   0.7762   0.0256
  -5.500  -0.4803   0.02150   0.01558  -0.0067   0.7733   0.0198
  -5.250  -0.4549   0.02199   0.01619  -0.0068   0.7686   0.0213
  -5.000  -0.4312   0.02061   0.01459  -0.0060   0.7637   0.0225
  -4.750  -0.4070   0.01882   0.01248  -0.0050   0.7597   0.0236
  -4.500  -0.3811   0.01781   0.01125  -0.0043   0.7551   0.0249
  -4.250  -0.3555   0.01597   0.00917  -0.0038   0.7501   0.0268
  -4.000  -0.3298   0.01522   0.00837  -0.0035   0.7459   0.0290
  -3.750  -0.3033   0.01454   0.00760  -0.0032   0.7417   0.0308
  -3.500  -0.2765   0.01386   0.00686  -0.0029   0.7365   0.0327
  -3.250  -0.2496   0.01361   0.00653  -0.0026   0.7321   0.0347
  -3.000  -0.2249   0.01243   0.00524  -0.0020   0.7281   0.0370
  -2.750  -0.1997   0.01181   0.00462  -0.0015   0.7229   0.0392
  -2.500  -0.1740   0.01145   0.00423  -0.0011   0.7183   0.0418
  -2.250  -0.1483   0.01114   0.00386  -0.0006   0.7145   0.0441
  -2.000  -0.1223   0.01082   0.00351  -0.0002   0.7095   0.0457
  -1.750  -0.0966   0.01050   0.00315   0.0002   0.7051   0.0475
  -1.500  -0.0713   0.01016   0.00278   0.0008   0.7015   0.0529
  -1.250  -0.0448   0.00997   0.00258   0.0011   0.6966   0.0580
  -1.000  -0.0191   0.00968   0.00234   0.0015   0.6915   0.0766
  -0.750  -0.0091   0.00805   0.00206   0.0044   0.6873   0.4675
  -0.500  -0.0092   0.00689   0.00225   0.0108   0.6827   0.8581
  -0.250   0.0137   0.00707   0.00245   0.0125   0.6780   0.8898
   0.000   0.0369   0.00722   0.00258   0.0141   0.6742   0.9111
   0.250   0.0616   0.00738   0.00274   0.0155   0.6704   0.9269
   0.500   0.0943   0.00762   0.00298   0.0151   0.6661   0.9399
   0.750   0.1513   0.00807   0.00338   0.0096   0.6621   0.9485
   1.000   0.2344   0.00870   0.00392  -0.0016   0.6586   0.9588
   1.250   0.2784   0.00881   0.00402  -0.0050   0.6542   0.9617
   1.500   0.3081   0.00878   0.00397  -0.0055   0.6477   0.9634
   1.750   0.3361   0.00876   0.00392  -0.0057   0.6401   0.9653
   2.000   0.3607   0.00871   0.00383  -0.0051   0.6317   0.9666
   2.250   0.3834   0.00864   0.00377  -0.0041   0.6230   0.9672
   2.500   0.4057   0.00859   0.00367  -0.0031   0.6144   0.9677
   2.750   0.4275   0.00851   0.00362  -0.0020   0.6050   0.9684
   3.000   0.4480   0.00848   0.00358  -0.0006   0.5978   0.9693
   3.250   0.4724   0.00844   0.00356   0.0000   0.5892   0.9701
   3.500   0.4992   0.00839   0.00352   0.0001   0.5761   0.9705
   3.750   0.5258   0.00837   0.00349   0.0001   0.5599   0.9708
   4.000   0.5524   0.00837   0.00348   0.0002   0.5417   0.9713
   4.250   0.5787   0.00841   0.00350   0.0003   0.5145   0.9718
   4.500   0.6036   0.00862   0.00354   0.0006   0.4560   0.9724
   4.750   0.6221   0.00967   0.00397   0.0014   0.3194   0.9734
   5.000   0.6390   0.01100   0.00458   0.0021   0.1632   0.9747
   5.250   0.6602   0.01176   0.00507   0.0026   0.0997   0.9759
   5.500   0.6823   0.01245   0.00550   0.0030   0.0519   0.9774
   5.750   0.7056   0.01288   0.00589   0.0034   0.0428   0.9789
   6.000   0.7278   0.01325   0.00633   0.0040   0.0398   0.9805
   6.250   0.7468   0.01373   0.00684   0.0053   0.0368   0.9824
   6.500   0.7691   0.01457   0.00779   0.0055   0.0328   0.9838
   6.750   0.7957   0.01509   0.00838   0.0051   0.0314   0.9847
   7.000   0.8210   0.01575   0.00911   0.0048   0.0291   0.9859
   7.250   0.8448   0.01652   0.00990   0.0046   0.0262   0.9874
   7.500   0.8598   0.01845   0.01193   0.0055   0.0237   0.9900
   7.750   0.8847   0.01893   0.01248   0.0054   0.0227   0.9918
   8.000   0.9077   0.01963   0.01326   0.0056   0.0214   0.9937
   8.250   0.9325   0.02048   0.01417   0.0053   0.0200   0.9953
   8.500   0.9586   0.02115   0.01486   0.0045   0.0184   0.9970
   8.750   0.9781   0.02364   0.01739   0.0049   0.0169   0.9983
   9.000   1.0041   0.02457   0.01846   0.0044   0.0164   0.9998
   9.250   1.0078   0.02502   0.01902   0.0082   0.0158   1.0000
   9.500   1.0057   0.02585   0.01994   0.0132   0.0156   1.0000
   9.750   1.0145   0.02689   0.02110   0.0160   0.0150   1.0000
  10.000   1.0268   0.02833   0.02268   0.0180   0.0145   1.0000
  10.250   1.0379   0.02952   0.02398   0.0200   0.0139   1.0000
  10.500   1.0448   0.03011   0.02461   0.0226   0.0133   1.0000
  10.750   1.0505   0.03119   0.02580   0.0250   0.0130   1.0000
  11.000   1.0559   0.03271   0.02736   0.0270   0.0123   1.0000
  11.250   1.0530   0.03701   0.03202   0.0294   0.0120   1.0000
  11.500   1.0497   0.03931   0.03455   0.0317   0.0119   1.0000
  11.750   1.0447   0.04159   0.03706   0.0338   0.0117   1.0000
  12.000   1.0375   0.04440   0.04009   0.0355   0.0117   1.0000
  12.250   1.0258   0.04789   0.04381   0.0369   0.0117   1.0000
  12.500   1.0116   0.05153   0.04769   0.0378   0.0116   1.0000
  12.750   0.9972   0.05532   0.05169   0.0382   0.0114   1.0000
  13.000   0.9787   0.05998   0.05654   0.0379   0.0116   1.0000
  13.250   0.9607   0.06476   0.06151   0.0368   0.0114   1.0000
  13.500   0.9379   0.07068   0.06761   0.0349   0.0115   1.0000
  13.750   0.9181   0.07658   0.07364   0.0324   0.0117   1.0000
  14.000   0.8131   0.07586   0.07305   0.0346   0.0121   1.0000
  14.250   0.7972   0.08201   0.07933   0.0317   0.0122   1.0000
  14.500   0.7772   0.08929   0.08675   0.0278   0.0123   1.0000
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