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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 100,000
Max Cl/Cd: 51.33 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1510-il-100000.txt
Download as CSV file: xf-hq1510-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4013   0.09800   0.09338  -0.0221   1.0000   0.1175
  -9.500  -0.4309   0.09378   0.08930  -0.0279   1.0000   0.1200
  -9.250  -0.4045   0.08930   0.08476  -0.0243   1.0000   0.1244
  -9.000  -0.4036   0.08549   0.08099  -0.0251   1.0000   0.1299
  -8.750  -0.4405   0.08075   0.07638  -0.0317   1.0000   0.1338
  -8.500  -0.4155   0.07650   0.07212  -0.0281   1.0000   0.1380
  -8.250  -0.4167   0.07261   0.06826  -0.0287   1.0000   0.1439
  -8.000  -0.4663   0.06735   0.06317  -0.0360   1.0000   0.1474
  -7.750  -0.4365   0.06371   0.05952  -0.0314   1.0000   0.1530
  -7.500  -0.4538   0.05946   0.05536  -0.0331   1.0000   0.1575
  -6.750  -0.5618   0.04404   0.03777  -0.0407   1.0000   0.0651
  -6.500  -0.5535   0.03975   0.03336  -0.0390   1.0000   0.0624
  -6.250  -0.5446   0.03602   0.02924  -0.0369   1.0000   0.0599
  -6.000  -0.5332   0.03259   0.02530  -0.0347   1.0000   0.0584
  -5.750  -0.5187   0.02983   0.02208  -0.0326   1.0000   0.0587
  -5.500  -0.5024   0.02797   0.01984  -0.0308   1.0000   0.0628
  -5.250  -0.4844   0.02617   0.01749  -0.0289   1.0000   0.0666
  -5.000  -0.4655   0.02396   0.01525  -0.0276   1.0000   0.0717
  -4.750  -0.4454   0.02250   0.01354  -0.0261   1.0000   0.0807
  -4.500  -0.4255   0.02132   0.01226  -0.0248   1.0000   0.0924
  -4.250  -0.4059   0.02000   0.01102  -0.0236   1.0000   0.1083
  -4.000  -0.3863   0.01899   0.01014  -0.0226   1.0000   0.1259
  -3.750  -0.3664   0.01806   0.00930  -0.0213   1.0000   0.1445
  -3.500  -0.3471   0.01719   0.00859  -0.0202   1.0000   0.1765
  -3.250  -0.3291   0.01551   0.00776  -0.0193   1.0000   0.2890
  -3.000  -0.3198   0.01434   0.00816  -0.0156   1.0000   0.6149
  -2.750  -0.3067   0.01454   0.00848  -0.0122   1.0000   0.6918
  -2.500  -0.2933   0.01476   0.00869  -0.0089   1.0000   0.7414
  -2.250  -0.2809   0.01492   0.00884  -0.0056   1.0000   0.7797
  -2.000  -0.2571   0.01519   0.00907  -0.0043   0.9950   0.8190
  -1.750  -0.2293   0.01541   0.00926  -0.0036   0.9870   0.8600
  -1.500  -0.1981   0.01566   0.00950  -0.0031   0.9799   0.9069
  -1.250  -0.1423   0.01600   0.00971  -0.0078   0.9750   0.9492
  -1.000  -0.0641   0.01641   0.00991  -0.0177   0.9728   0.9756
  -0.750   0.0146   0.01668   0.00998  -0.0281   0.9708   0.9945
  -0.500   0.0585   0.01671   0.00990  -0.0329   0.9620   1.0000
  -0.250   0.0975   0.01676   0.00987  -0.0366   0.9526   1.0000
   0.000   0.1330   0.01680   0.00983  -0.0395   0.9425   1.0000
   0.250   0.1621   0.01685   0.00982  -0.0410   0.9310   1.0000
   0.500   0.1958   0.01694   0.00987  -0.0432   0.9208   1.0000
   0.750   0.2505   0.01694   0.00984  -0.0485   0.9134   1.0000
   1.000   0.2954   0.01681   0.00970  -0.0519   0.9012   1.0000
   1.250   0.3422   0.01652   0.00943  -0.0550   0.8880   1.0000
   1.500   0.3800   0.01630   0.00922  -0.0564   0.8748   1.0000
   1.750   0.4112   0.01622   0.00915  -0.0568   0.8622   1.0000
   2.000   0.4411   0.01617   0.00911  -0.0569   0.8500   1.0000
   2.250   0.4704   0.01609   0.00908  -0.0567   0.8374   1.0000
   2.500   0.4984   0.01602   0.00903  -0.0561   0.8242   1.0000
   2.750   0.5250   0.01594   0.00899  -0.0552   0.8100   1.0000
   3.000   0.5507   0.01586   0.00895  -0.0540   0.7947   1.0000
   3.250   0.5764   0.01575   0.00891  -0.0528   0.7783   1.0000
   3.500   0.6025   0.01558   0.00878  -0.0515   0.7612   1.0000
   3.750   0.6294   0.01534   0.00857  -0.0501   0.7433   1.0000
   4.000   0.6527   0.01522   0.00851  -0.0484   0.7198   1.0000
   4.250   0.6772   0.01501   0.00837  -0.0467   0.6939   1.0000
   4.500   0.7012   0.01480   0.00815  -0.0448   0.6625   1.0000
   4.750   0.7239   0.01467   0.00799  -0.0428   0.6224   1.0000
   5.000   0.7457   0.01467   0.00786  -0.0408   0.5724   1.0000
   5.250   0.7659   0.01492   0.00793  -0.0387   0.5122   1.0000
   5.500   0.7853   0.01545   0.00817  -0.0368   0.4516   1.0000
   5.750   0.8043   0.01616   0.00860  -0.0352   0.3969   1.0000
   6.000   0.8231   0.01696   0.00914  -0.0336   0.3477   1.0000
   6.250   0.8410   0.01784   0.00981  -0.0321   0.2982   1.0000
   6.500   0.8572   0.01900   0.01073  -0.0304   0.2464   1.0000
   6.750   0.8718   0.02039   0.01180  -0.0285   0.1889   1.0000
   7.000   0.8881   0.02176   0.01286  -0.0269   0.1513   1.0000
   7.250   0.9073   0.02317   0.01414  -0.0256   0.1302   1.0000
   7.500   0.9282   0.02465   0.01553  -0.0246   0.1160   1.0000
   7.750   0.9501   0.02613   0.01702  -0.0237   0.1043   1.0000
   8.000   0.9748   0.02807   0.01900  -0.0232   0.0966   1.0000
   8.250   0.9993   0.02992   0.02098  -0.0226   0.0897   1.0000
   8.500   1.0212   0.03207   0.02335  -0.0217   0.0822   1.0000
   8.750   1.0436   0.03441   0.02574  -0.0212   0.0755   1.0000
   9.000   1.0577   0.03617   0.02787  -0.0195   0.0666   1.0000
   9.250   1.0705   0.03861   0.03052  -0.0180   0.0586   1.0000
   9.500   1.0842   0.04056   0.03254  -0.0168   0.0510   1.0000
   9.750   1.0888   0.04458   0.03711  -0.0143   0.0476   1.0000
  10.000   1.0896   0.04829   0.04139  -0.0116   0.0457   1.0000
  10.250   1.0857   0.05221   0.04578  -0.0089   0.0446   1.0000
  10.500   1.0763   0.05621   0.05018  -0.0062   0.0442   1.0000
  10.750   1.0604   0.05997   0.05426  -0.0033   0.0443   1.0000
  11.000   1.0403   0.06378   0.05833  -0.0009   0.0446   1.0000
  11.250   1.0173   0.06808   0.06287   0.0001   0.0448   1.0000
  11.500   0.9946   0.07294   0.06792  -0.0005   0.0455   1.0000
  11.750   0.9698   0.07870   0.07385  -0.0026   0.0460   1.0000
  12.000   0.9451   0.08538   0.08066  -0.0062   0.0467   1.0000
  12.250   0.9221   0.09296   0.08833  -0.0110   0.0476   1.0000
  12.500   0.9037   0.10088   0.09629  -0.0158   0.0485   1.0000
  12.750   0.8867   0.10963   0.10505  -0.0207   0.0492   1.0000
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