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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 500,000
Max Cl/Cd: 73.27 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1510-il-500000-n5.txt
Download as CSV file: xf-hq1510-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7672   0.04764   0.04504  -0.0503   1.0000   0.0040
 -11.000  -0.7886   0.04234   0.03958  -0.0535   1.0000   0.0039
 -10.750  -0.8110   0.03850   0.03554  -0.0528   1.0000   0.0039
 -10.500  -0.8214   0.03505   0.03179  -0.0513   1.0000   0.0040
 -10.250  -0.8243   0.03182   0.02824  -0.0499   1.0000   0.0040
 -10.000  -0.8192   0.02924   0.02535  -0.0485   1.0000   0.0041
  -9.750  -0.8100   0.02706   0.02289  -0.0471   1.0000   0.0041
  -9.500  -0.8022   0.02454   0.02004  -0.0453   1.0000   0.0043
  -9.250  -0.7901   0.02269   0.01794  -0.0438   1.0000   0.0045
  -9.000  -0.7744   0.02145   0.01654  -0.0424   1.0000   0.0046
  -8.750  -0.7578   0.02040   0.01536  -0.0410   1.0000   0.0048
  -8.500  -0.7292   0.01938   0.01421  -0.0420   0.9959   0.0051
  -8.250  -0.7000   0.01828   0.01295  -0.0430   0.9904   0.0054
  -8.000  -0.6692   0.01724   0.01175  -0.0443   0.9856   0.0057
  -7.750  -0.6389   0.01634   0.01070  -0.0454   0.9800   0.0062
  -7.500  -0.6074   0.01569   0.00994  -0.0466   0.9743   0.0067
  -7.250  -0.5780   0.01463   0.00873  -0.0475   0.9672   0.0075
  -7.000  -0.5473   0.01391   0.00792  -0.0485   0.9597   0.0081
  -6.750  -0.5178   0.01328   0.00721  -0.0491   0.9506   0.0088
  -6.500  -0.4884   0.01272   0.00655  -0.0497   0.9411   0.0095
  -6.250  -0.4603   0.01225   0.00597  -0.0499   0.9302   0.0103
  -6.000  -0.4337   0.01171   0.00535  -0.0497   0.9190   0.0120
  -5.750  -0.4073   0.01132   0.00490  -0.0495   0.9087   0.0141
  -5.500  -0.3811   0.01096   0.00446  -0.0492   0.8990   0.0172
  -5.250  -0.3549   0.01065   0.00412  -0.0489   0.8894   0.0230
  -5.000  -0.3288   0.01036   0.00382  -0.0486   0.8800   0.0298
  -4.750  -0.3022   0.01016   0.00356  -0.0484   0.8715   0.0354
  -4.500  -0.2757   0.00992   0.00332  -0.0482   0.8629   0.0429
  -4.250  -0.2490   0.00972   0.00306  -0.0480   0.8549   0.0498
  -4.000  -0.2224   0.00950   0.00285  -0.0477   0.8471   0.0617
  -3.750  -0.1956   0.00928   0.00263  -0.0476   0.8394   0.0749
  -3.250  -0.1420   0.00881   0.00223  -0.0473   0.8240   0.1176
  -3.000  -0.1156   0.00853   0.00205  -0.0471   0.8165   0.1585
  -2.750  -0.0892   0.00818   0.00188  -0.0470   0.8083   0.2162
  -2.500  -0.0631   0.00780   0.00170  -0.0469   0.8004   0.2854
  -2.250  -0.0375   0.00737   0.00154  -0.0467   0.7918   0.3783
  -2.000  -0.0116   0.00700   0.00145  -0.0465   0.7833   0.4670
  -1.750   0.0148   0.00681   0.00140  -0.0462   0.7751   0.5265
  -1.500   0.0420   0.00670   0.00137  -0.0460   0.7662   0.5641
  -1.250   0.0688   0.00662   0.00134  -0.0457   0.7556   0.6028
  -1.000   0.0955   0.00657   0.00134  -0.0453   0.7430   0.6370
  -0.750   0.1228   0.00656   0.00132  -0.0451   0.7311   0.6551
  -0.500   0.1502   0.00656   0.00130  -0.0449   0.7200   0.6695
  -0.250   0.1778   0.00656   0.00129  -0.0448   0.7087   0.6832
   0.000   0.2052   0.00657   0.00130  -0.0446   0.6970   0.6974
   0.250   0.2325   0.00659   0.00131  -0.0444   0.6853   0.7115
   0.500   0.2599   0.00662   0.00132  -0.0442   0.6722   0.7221
   0.750   0.2874   0.00666   0.00133  -0.0440   0.6586   0.7308
   1.000   0.3148   0.00670   0.00136  -0.0439   0.6465   0.7389
   1.250   0.3423   0.00675   0.00139  -0.0438   0.6333   0.7475
   1.500   0.3695   0.00681   0.00143  -0.0436   0.6175   0.7562
   1.750   0.3967   0.00687   0.00148  -0.0434   0.6008   0.7650
   2.000   0.4235   0.00696   0.00154  -0.0431   0.5806   0.7747
   2.250   0.4500   0.00706   0.00161  -0.0428   0.5569   0.7842
   2.500   0.4761   0.00720   0.00170  -0.0424   0.5289   0.7941
   2.750   0.5016   0.00740   0.00180  -0.0420   0.4941   0.8046
   3.000   0.5264   0.00766   0.00193  -0.0414   0.4523   0.8157
   3.250   0.5506   0.00798   0.00211  -0.0408   0.4033   0.8276
   3.500   0.5739   0.00838   0.00232  -0.0401   0.3447   0.8409
   3.750   0.5964   0.00886   0.00256  -0.0393   0.2835   0.8563
   4.000   0.6202   0.00912   0.00277  -0.0386   0.2540   0.8753
   4.250   0.6448   0.00926   0.00297  -0.0379   0.2378   0.9042
   4.500   0.6781   0.00944   0.00318  -0.0391   0.2202   0.9533
   4.750   0.7120   0.00973   0.00341  -0.0407   0.1996   1.0000
   5.000   0.7371   0.01006   0.00364  -0.0404   0.1743   1.0000
   5.250   0.7614   0.01047   0.00393  -0.0399   0.1438   1.0000
   5.500   0.7849   0.01098   0.00427  -0.0394   0.1091   1.0000
   5.750   0.8077   0.01157   0.00467  -0.0388   0.0767   1.0000
   6.000   0.8316   0.01203   0.00504  -0.0383   0.0593   1.0000
   6.250   0.8561   0.01241   0.00539  -0.0379   0.0501   1.0000
   6.500   0.8804   0.01281   0.00579  -0.0374   0.0431   1.0000
   6.750   0.9051   0.01315   0.00615  -0.0370   0.0383   1.0000
   7.000   0.9289   0.01358   0.00656  -0.0365   0.0325   1.0000
   7.250   0.9529   0.01397   0.00695  -0.0360   0.0265   1.0000
   7.500   0.9764   0.01443   0.00738  -0.0355   0.0217   1.0000
   7.750   1.0000   0.01484   0.00782  -0.0349   0.0178   1.0000
   8.000   1.0227   0.01535   0.00832  -0.0343   0.0133   1.0000
   8.250   1.0440   0.01600   0.00897  -0.0334   0.0070   1.0000
   8.500   1.0650   0.01668   0.00966  -0.0325   0.0053   1.0000
   8.750   1.0861   0.01732   0.01036  -0.0316   0.0047   1.0000
   9.000   1.1065   0.01802   0.01114  -0.0306   0.0042   1.0000
   9.250   1.1263   0.01876   0.01199  -0.0296   0.0039   1.0000
   9.500   1.1458   0.01949   0.01283  -0.0285   0.0037   1.0000
   9.750   1.1647   0.02023   0.01367  -0.0273   0.0035   1.0000
  10.000   1.1824   0.02104   0.01459  -0.0261   0.0034   1.0000
  10.250   1.1993   0.02188   0.01555  -0.0247   0.0032   1.0000
  10.500   1.2150   0.02277   0.01655  -0.0233   0.0030   1.0000
  10.750   1.2288   0.02373   0.01762  -0.0216   0.0029   1.0000
  11.000   1.2388   0.02475   0.01876  -0.0193   0.0028   1.0000
  11.250   1.2471   0.02582   0.01995  -0.0168   0.0027   1.0000
  11.500   1.2538   0.02701   0.02127  -0.0144   0.0026   1.0000
  11.750   1.2587   0.02838   0.02276  -0.0121   0.0026   1.0000
  12.000   1.2626   0.02986   0.02438  -0.0100   0.0025   1.0000
  12.250   1.2644   0.03160   0.02625  -0.0080   0.0025   1.0000
  12.500   1.2655   0.03348   0.02827  -0.0063   0.0024   1.0000
  12.750   1.2647   0.03565   0.03059  -0.0049   0.0024   1.0000
  13.000   1.2611   0.03823   0.03333  -0.0038   0.0023   1.0000
  13.250   1.2526   0.04153   0.03680  -0.0030   0.0023   1.0000
  13.500   1.2472   0.04472   0.04017  -0.0029   0.0023   1.0000
  13.750   1.2377   0.04866   0.04428  -0.0033   0.0022   1.0000
  14.000   1.2294   0.05275   0.04853  -0.0043   0.0022   1.0000
  14.500   1.1886   0.06576   0.06195  -0.0097   0.0021   1.0000
  14.750   1.1826   0.07075   0.06707  -0.0124   0.0022   1.0000
  15.000   1.1714   0.07705   0.07351  -0.0159   0.0022   1.0000
  15.250   1.1551   0.08473   0.08136  -0.0204   0.0022   1.0000
  15.500   1.1387   0.09284   0.08961  -0.0251   0.0022   1.0000
  15.750   1.1155   0.10271   0.09965  -0.0308   0.0022   1.0000
  16.000   1.1085   0.10918   0.10622  -0.0344   0.0023   1.0000
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