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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 200,000
Max Cl/Cd: 58.3 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1585-il-200000-n5.txt
Download as CSV file: xf-hq1585-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8.5 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5447   0.08732   0.08381  -0.0180   1.0000   0.0126
  -9.250  -0.5500   0.08165   0.07822  -0.0213   1.0000   0.0126
  -9.000  -0.5581   0.07535   0.07198  -0.0254   1.0000   0.0123
  -8.750  -0.5717   0.06721   0.06392  -0.0324   1.0000   0.0123
  -8.500  -0.5923   0.05815   0.05477  -0.0401   1.0000   0.0118
  -8.250  -0.6064   0.05028   0.04665  -0.0436   1.0000   0.0115
  -8.000  -0.6102   0.04421   0.04025  -0.0448   1.0000   0.0116
  -7.750  -0.6069   0.03914   0.03479  -0.0450   1.0000   0.0120
  -7.500  -0.5988   0.03474   0.02996  -0.0446   1.0000   0.0124
  -7.250  -0.5854   0.03161   0.02643  -0.0439   1.0000   0.0137
  -7.000  -0.5707   0.02848   0.02279  -0.0427   1.0000   0.0149
  -6.750  -0.5541   0.02604   0.01988  -0.0415   1.0000   0.0156
  -6.500  -0.5386   0.02314   0.01654  -0.0401   1.0000   0.0164
  -6.250  -0.5211   0.02160   0.01485  -0.0388   1.0000   0.0174
  -6.000  -0.4922   0.02049   0.01358  -0.0397   0.9957   0.0190
  -5.750  -0.4587   0.01959   0.01248  -0.0412   0.9893   0.0219
  -5.500  -0.4250   0.01836   0.01100  -0.0426   0.9837   0.0234
  -5.250  -0.3934   0.01671   0.00921  -0.0438   0.9776   0.0256
  -5.000  -0.3611   0.01594   0.00839  -0.0451   0.9709   0.0286
  -4.750  -0.3282   0.01506   0.00739  -0.0464   0.9649   0.0308
  -4.500  -0.2969   0.01432   0.00654  -0.0473   0.9574   0.0331
  -4.250  -0.2637   0.01373   0.00584  -0.0485   0.9515   0.0352
  -4.000  -0.2335   0.01305   0.00514  -0.0493   0.9435   0.0410
  -3.750  -0.2010   0.01262   0.00461  -0.0503   0.9374   0.0482
  -3.500  -0.1717   0.01212   0.00407  -0.0507   0.9293   0.0612
  -3.250  -0.1416   0.01154   0.00364  -0.0515   0.9229   0.0984
  -3.000  -0.1152   0.01083   0.00335  -0.0517   0.9145   0.2031
  -2.750  -0.0885   0.01006   0.00312  -0.0520   0.9076   0.3398
  -2.500  -0.0645   0.00940   0.00304  -0.0515   0.8994   0.4908
  -2.250  -0.0390   0.00911   0.00305  -0.0508   0.8926   0.5870
  -2.000  -0.0135   0.00899   0.00306  -0.0500   0.8849   0.6435
  -1.750   0.0127   0.00895   0.00308  -0.0493   0.8782   0.6860
  -1.500   0.0391   0.00894   0.00305  -0.0488   0.8707   0.7129
  -1.250   0.0661   0.00893   0.00301  -0.0483   0.8639   0.7307
  -1.000   0.0927   0.00891   0.00296  -0.0478   0.8556   0.7469
  -0.750   0.1190   0.00889   0.00290  -0.0472   0.8458   0.7629
  -0.500   0.1450   0.00887   0.00284  -0.0465   0.8362   0.7809
  -0.250   0.1707   0.00883   0.00280  -0.0457   0.8264   0.7971
   0.000   0.1962   0.00879   0.00276  -0.0449   0.8154   0.8122
   0.250   0.2211   0.00873   0.00272  -0.0438   0.8035   0.8299
   0.500   0.2460   0.00868   0.00269  -0.0428   0.7904   0.8477
   0.750   0.2718   0.00864   0.00265  -0.0420   0.7773   0.8637
   1.000   0.2985   0.00862   0.00265  -0.0415   0.7655   0.8799
   1.250   0.3264   0.00859   0.00264  -0.0412   0.7549   0.8986
   1.500   0.3567   0.00856   0.00265  -0.0415   0.7425   0.9217
   1.750   0.3915   0.00854   0.00267  -0.0429   0.7293   0.9499
   2.000   0.4286   0.00853   0.00268  -0.0448   0.7138   0.9962
   2.250   0.4556   0.00859   0.00272  -0.0446   0.6964   1.0000
   2.500   0.4820   0.00868   0.00277  -0.0443   0.6758   1.0000
   2.750   0.5071   0.00881   0.00277  -0.0435   0.6365   1.0000
   3.000   0.5305   0.00910   0.00277  -0.0425   0.5734   1.0000
   3.250   0.5528   0.00958   0.00286  -0.0414   0.4887   1.0000
   3.500   0.5756   0.01011   0.00306  -0.0406   0.4204   1.0000
   3.750   0.5987   0.01068   0.00337  -0.0399   0.3565   1.0000
   4.000   0.6226   0.01121   0.00367  -0.0395   0.3078   1.0000
   4.250   0.6472   0.01166   0.00399  -0.0391   0.2701   1.0000
   4.500   0.6713   0.01219   0.00434  -0.0387   0.2263   1.0000
   4.750   0.6957   0.01269   0.00471  -0.0383   0.1917   1.0000
   5.000   0.7199   0.01324   0.00511  -0.0379   0.1496   1.0000
   5.250   0.7427   0.01400   0.00566  -0.0374   0.1006   1.0000
   5.500   0.7656   0.01477   0.00625  -0.0368   0.0670   1.0000
   5.750   0.7895   0.01538   0.00684  -0.0363   0.0562   1.0000
   6.000   0.8136   0.01598   0.00747  -0.0358   0.0513   1.0000
   6.250   0.8373   0.01659   0.00815  -0.0352   0.0478   1.0000
   6.500   0.8613   0.01714   0.00878  -0.0348   0.0422   1.0000
   6.750   0.8835   0.01793   0.00963  -0.0342   0.0362   1.0000
   7.000   0.9075   0.01846   0.01031  -0.0336   0.0333   1.0000
   7.250   0.9307   0.01909   0.01105  -0.0331   0.0286   1.0000
   7.500   0.9526   0.01991   0.01194  -0.0324   0.0228   1.0000
   7.750   0.9756   0.02055   0.01264  -0.0319   0.0176   1.0000
   8.000   0.9960   0.02159   0.01379  -0.0309   0.0148   1.0000
   8.250   1.0164   0.02259   0.01490  -0.0300   0.0131   1.0000
   8.500   1.0358   0.02367   0.01610  -0.0290   0.0119   1.0000
   8.750   1.0525   0.02519   0.01775  -0.0277   0.0111   1.0000
   9.000   1.0700   0.02661   0.01938  -0.0265   0.0103   1.0000
   9.250   1.0873   0.02800   0.02095  -0.0253   0.0094   1.0000
   9.500   1.1038   0.02936   0.02248  -0.0242   0.0087   1.0000
   9.750   1.1176   0.03110   0.02443  -0.0227   0.0082   1.0000
  10.000   1.1293   0.03304   0.02659  -0.0212   0.0079   1.0000
  10.250   1.1378   0.03522   0.02902  -0.0194   0.0076   1.0000
  10.500   1.1421   0.03771   0.03180  -0.0173   0.0075   1.0000
  10.750   1.1391   0.04044   0.03482  -0.0146   0.0073   1.0000
  11.000   1.1326   0.04335   0.03800  -0.0121   0.0072   1.0000
  11.250   1.1220   0.04671   0.04165  -0.0101   0.0072   1.0000
  11.500   1.1071   0.05071   0.04594  -0.0091   0.0071   1.0000
  11.750   1.0922   0.05503   0.05051  -0.0091   0.0071   1.0000
  12.000   1.0797   0.05945   0.05515  -0.0101   0.0071   1.0000
  12.250   1.0611   0.06531   0.06124  -0.0126   0.0071   1.0000
  12.500   1.0444   0.07170   0.06784  -0.0164   0.0071   1.0000
  12.750   1.0281   0.07903   0.07536  -0.0213   0.0072   1.0000
  13.000   1.0068   0.08872   0.08523  -0.0282   0.0073   1.0000
  13.250   0.9755   0.10266   0.09940  -0.0375   0.0076   1.0000
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