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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 500,000
Max Cl/Cd: 88.38 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1510-il-500000.txt
Download as CSV file: xf-hq1510-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5109   0.08349   0.08126  -0.0314   1.0000   0.0211
  -9.500  -0.5183   0.07477   0.07256  -0.0377   1.0000   0.0211
  -9.250  -0.5341   0.06678   0.06451  -0.0451   1.0000   0.0211
  -9.000  -0.5481   0.06229   0.05996  -0.0483   1.0000   0.0211
  -8.750  -0.6224   0.04803   0.04549  -0.0494   1.0000   0.0139
  -8.500  -0.6962   0.03040   0.02657  -0.0450   1.0000   0.0105
  -8.250  -0.6916   0.02728   0.02310  -0.0426   1.0000   0.0106
  -8.000  -0.6837   0.02505   0.02061  -0.0402   1.0000   0.0108
  -7.750  -0.6765   0.02292   0.01819  -0.0372   1.0000   0.0107
  -7.500  -0.6541   0.02150   0.01662  -0.0373   0.9984   0.0113
  -7.250  -0.6200   0.02032   0.01528  -0.0393   0.9953   0.0121
  -7.000  -0.5871   0.01876   0.01348  -0.0410   0.9918   0.0127
  -6.750  -0.5549   0.01690   0.01138  -0.0423   0.9878   0.0131
  -6.500  -0.5207   0.01551   0.00980  -0.0439   0.9846   0.0138
  -6.250  -0.4845   0.01456   0.00871  -0.0458   0.9823   0.0146
  -6.000  -0.4552   0.01287   0.00688  -0.0467   0.9764   0.0164
  -5.750  -0.4202   0.01223   0.00621  -0.0484   0.9725   0.0186
  -5.500  -0.3848   0.01157   0.00546  -0.0502   0.9690   0.0228
  -5.250  -0.3545   0.01112   0.00501  -0.0507   0.9611   0.0293
  -5.000  -0.3218   0.01063   0.00451  -0.0518   0.9555   0.0407
  -4.750  -0.2942   0.01023   0.00412  -0.0519   0.9459   0.0509
  -4.500  -0.2658   0.00989   0.00376  -0.0520   0.9377   0.0600
  -4.250  -0.2388   0.00959   0.00343  -0.0518   0.9286   0.0706
  -4.000  -0.2129   0.00926   0.00315  -0.0514   0.9190   0.0896
  -3.750  -0.1875   0.00880   0.00284  -0.0511   0.9104   0.1313
  -3.500  -0.1632   0.00823   0.00257  -0.0506   0.9011   0.2177
  -3.250  -0.1394   0.00758   0.00231  -0.0502   0.8919   0.3295
  -3.000  -0.1158   0.00699   0.00215  -0.0496   0.8836   0.4621
  -2.750  -0.0904   0.00674   0.00208  -0.0490   0.8744   0.5334
  -2.500  -0.0642   0.00662   0.00204  -0.0486   0.8662   0.5781
  -2.250  -0.0375   0.00656   0.00198  -0.0481   0.8578   0.6103
  -2.000  -0.0108   0.00652   0.00197  -0.0477   0.8491   0.6403
  -1.750   0.0161   0.00650   0.00194  -0.0473   0.8415   0.6625
  -1.500   0.0433   0.00648   0.00191  -0.0471   0.8326   0.6785
  -1.250   0.0702   0.00649   0.00190  -0.0466   0.8234   0.7001
  -1.000   0.0966   0.00648   0.00189  -0.0461   0.8137   0.7194
  -0.750   0.1236   0.00646   0.00188  -0.0457   0.8031   0.7328
  -0.500   0.1509   0.00646   0.00185  -0.0454   0.7937   0.7449
  -0.250   0.1781   0.00648   0.00183  -0.0451   0.7848   0.7574
   0.000   0.2052   0.00646   0.00184  -0.0448   0.7748   0.7699
   0.250   0.2321   0.00646   0.00184  -0.0444   0.7646   0.7821
   0.500   0.2591   0.00646   0.00183  -0.0441   0.7547   0.7924
   0.750   0.2865   0.00646   0.00182  -0.0439   0.7449   0.8019
   1.000   0.3138   0.00646   0.00183  -0.0436   0.7345   0.8118
   1.250   0.3408   0.00645   0.00185  -0.0433   0.7244   0.8215
   1.500   0.3678   0.00646   0.00185  -0.0430   0.7138   0.8321
   1.750   0.3946   0.00646   0.00187  -0.0427   0.7020   0.8437
   2.000   0.4212   0.00646   0.00190  -0.0423   0.6896   0.8563
   2.250   0.4473   0.00645   0.00194  -0.0418   0.6761   0.8703
   2.500   0.4729   0.00644   0.00197  -0.0411   0.6613   0.8868
   2.750   0.4982   0.00645   0.00201  -0.0404   0.6446   0.9081
   3.000   0.5266   0.00645   0.00206  -0.0403   0.6229   0.9378
   3.250   0.5642   0.00656   0.00212  -0.0423   0.5910   0.9707
   3.500   0.6010   0.00680   0.00218  -0.0445   0.5422   1.0000
   3.750   0.6239   0.00716   0.00230  -0.0437   0.4874   1.0000
   4.000   0.6467   0.00760   0.00250  -0.0429   0.4281   1.0000
   4.250   0.6699   0.00807   0.00272  -0.0423   0.3739   1.0000
   4.500   0.6935   0.00852   0.00297  -0.0417   0.3250   1.0000
   4.750   0.7175   0.00895   0.00323  -0.0412   0.2886   1.0000
   5.000   0.7419   0.00935   0.00351  -0.0407   0.2606   1.0000
   5.250   0.7664   0.00973   0.00380  -0.0403   0.2356   1.0000
   5.500   0.7912   0.01009   0.00407  -0.0399   0.2099   1.0000
   5.750   0.8155   0.01049   0.00436  -0.0394   0.1792   1.0000
   6.000   0.8386   0.01103   0.00471  -0.0388   0.1376   1.0000
   6.250   0.8601   0.01175   0.00521  -0.0380   0.0954   1.0000
   6.500   0.8823   0.01241   0.00573  -0.0373   0.0713   1.0000
   6.750   0.9053   0.01295   0.00623  -0.0366   0.0587   1.0000
   7.000   0.9275   0.01359   0.00683  -0.0358   0.0502   1.0000
   7.250   0.9519   0.01394   0.00723  -0.0354   0.0456   1.0000
   7.500   0.9741   0.01453   0.00780  -0.0346   0.0393   1.0000
   7.750   0.9982   0.01489   0.00823  -0.0341   0.0360   1.0000
   8.000   1.0218   0.01530   0.00867  -0.0336   0.0328   1.0000
   8.250   1.0425   0.01601   0.00939  -0.0326   0.0282   1.0000
   8.500   1.0677   0.01620   0.00964  -0.0324   0.0252   1.0000
   8.750   1.0900   0.01671   0.01012  -0.0317   0.0180   1.0000
   9.000   1.1087   0.01762   0.01102  -0.0304   0.0123   1.0000
   9.250   1.1278   0.01845   0.01188  -0.0292   0.0100   1.0000
   9.500   1.1419   0.01974   0.01332  -0.0273   0.0088   1.0000
   9.750   1.1586   0.02069   0.01439  -0.0258   0.0085   1.0000
  10.000   1.1736   0.02173   0.01556  -0.0241   0.0081   1.0000
  10.250   1.1876   0.02280   0.01674  -0.0223   0.0077   1.0000
  10.500   1.2015   0.02377   0.01781  -0.0206   0.0073   1.0000
  10.750   1.2116   0.02481   0.01895  -0.0182   0.0070   1.0000
  11.000   1.2183   0.02603   0.02028  -0.0156   0.0069   1.0000
  11.250   1.2251   0.02722   0.02155  -0.0132   0.0065   1.0000
  11.500   1.2286   0.02874   0.02320  -0.0107   0.0063   1.0000
  11.750   1.2277   0.03075   0.02536  -0.0081   0.0062   1.0000
  12.000   1.2257   0.03300   0.02779  -0.0058   0.0061   1.0000
  12.250   1.2194   0.03584   0.03084  -0.0037   0.0060   1.0000
  12.500   1.2152   0.03858   0.03380  -0.0022   0.0059   1.0000
  12.750   1.2061   0.04205   0.03749  -0.0010   0.0059   1.0000
  13.000   1.1979   0.04555   0.04119  -0.0004   0.0059   1.0000
  13.250   1.1933   0.04875   0.04456  -0.0005   0.0059   1.0000
  13.500   1.1833   0.05287   0.04888  -0.0011   0.0058   1.0000
  13.750   1.1746   0.05708   0.05326  -0.0023   0.0058   1.0000
  14.000   1.1570   0.06297   0.05935  -0.0044   0.0058   1.0000
  14.250   1.1472   0.06810   0.06465  -0.0070   0.0058   1.0000
  14.500   1.1283   0.07522   0.07197  -0.0108   0.0058   1.0000
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