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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 50,000
Max Cl/Cd: 33.18 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1511-il-50000.txt
Download as CSV file: xf-hq1511-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4588   0.11862   0.11148  -0.0075   1.0000   0.2651
 -10.000  -0.4612   0.11557   0.10850  -0.0083   1.0000   0.2751
  -9.750  -0.4765   0.11431   0.10735  -0.0095   1.0000   0.2870
  -9.500  -0.4620   0.11003   0.10305  -0.0088   1.0000   0.3013
  -9.250  -0.4618   0.10705   0.10013  -0.0086   1.0000   0.3167
  -9.000  -0.4447   0.10230   0.09538  -0.0076   1.0000   0.3338
  -8.750  -0.4285   0.09849   0.09157  -0.0065   1.0000   0.3547
  -8.500  -0.4278   0.09560   0.08873  -0.0059   1.0000   0.3728
  -8.250  -0.4216   0.09218   0.08534  -0.0055   1.0000   0.3869
  -8.000  -0.5557   0.07051   0.06405  -0.0398   1.0000   0.1502
  -7.750  -0.5981   0.06219   0.05526  -0.0440   1.0000   0.1272
  -7.500  -0.5955   0.05794   0.05084  -0.0431   1.0000   0.1249
  -7.250  -0.5939   0.05377   0.04648  -0.0420   1.0000   0.1236
  -7.000  -0.5922   0.04978   0.04218  -0.0406   1.0000   0.1230
  -6.750  -0.5893   0.04607   0.03800  -0.0389   1.0000   0.1243
  -6.500  -0.5846   0.04276   0.03398  -0.0369   1.0000   0.1265
  -6.250  -0.5712   0.04019   0.03158  -0.0352   1.0000   0.1365
  -6.000  -0.5597   0.03714   0.02777  -0.0333   1.0000   0.1406
  -5.750  -0.5438   0.03483   0.02552  -0.0317   1.0000   0.1508
  -5.500  -0.5260   0.03228   0.02249  -0.0302   1.0000   0.1565
  -5.250  -0.5075   0.03056   0.02051  -0.0287   1.0000   0.1674
  -5.000  -0.4878   0.02885   0.01873  -0.0273   1.0000   0.1784
  -4.750  -0.4672   0.02729   0.01707  -0.0259   1.0000   0.1912
  -4.500  -0.4468   0.02596   0.01567  -0.0245   1.0000   0.2100
  -4.250  -0.4263   0.02456   0.01439  -0.0229   1.0000   0.2328
  -4.000  -0.4068   0.02316   0.01319  -0.0214   1.0000   0.2733
  -3.750  -0.3910   0.02093   0.01211  -0.0194   1.0000   0.3874
  -3.500  -0.3946   0.02058   0.01325  -0.0103   1.0000   0.6437
  -3.250  -0.3935   0.02124   0.01396  -0.0022   1.0000   0.7261
  -3.000  -0.3909   0.02161   0.01430   0.0050   1.0000   0.7820
  -2.750  -0.3861   0.02178   0.01439   0.0117   1.0000   0.8311
  -2.500  -0.3697   0.02201   0.01447   0.0167   1.0000   0.8857
  -2.250  -0.1359   0.02366   0.01491  -0.0148   1.0000   0.9794
  -2.000  -0.0670   0.02312   0.01402  -0.0247   1.0000   1.0000
  -1.750  -0.0770   0.02288   0.01374  -0.0210   1.0000   1.0000
  -1.500  -0.0871   0.02261   0.01343  -0.0173   1.0000   1.0000
  -1.250  -0.0975   0.02228   0.01306  -0.0135   1.0000   1.0000
  -1.000  -0.1081   0.02190   0.01264  -0.0095   1.0000   1.0000
  -0.750  -0.1168   0.02150   0.01219  -0.0058   1.0000   1.0000
  -0.500  -0.1178   0.02125   0.01183  -0.0032   1.0000   1.0000
  -0.250  -0.1076   0.02125   0.01168  -0.0022   1.0000   1.0000
   0.000  -0.0919   0.02142   0.01170  -0.0021   1.0000   1.0000
   0.250  -0.0739   0.02171   0.01183  -0.0022   1.0000   1.0000
   0.500  -0.0548   0.02208   0.01207  -0.0024   1.0000   1.0000
   0.750  -0.0356   0.02253   0.01241  -0.0026   1.0000   1.0000
   1.000  -0.0162   0.02304   0.01281  -0.0029   1.0000   1.0000
   1.250   0.0029   0.02362   0.01330  -0.0032   1.0000   1.0000
   1.500   0.0279   0.02439   0.01401  -0.0046   0.9971   1.0000
   1.750   0.0783   0.02589   0.01545  -0.0107   0.9834   1.0000
   2.000   0.1254   0.02715   0.01670  -0.0160   0.9665   1.0000
   2.250   0.1896   0.02859   0.01816  -0.0238   0.9419   1.0000
   2.500   0.2452   0.02948   0.01911  -0.0294   0.9145   1.0000
   2.750   0.2921   0.03020   0.01990  -0.0332   0.8903   1.0000
   3.000   0.3453   0.03086   0.02069  -0.0377   0.8692   1.0000
   3.250   0.3825   0.03144   0.02137  -0.0397   0.8476   1.0000
   3.500   0.4283   0.03187   0.02195  -0.0425   0.8266   1.0000
   3.750   0.4713   0.03218   0.02245  -0.0446   0.8047   1.0000
   4.000   0.5183   0.03222   0.02270  -0.0469   0.7820   1.0000
   4.250   0.5613   0.03209   0.02281  -0.0480   0.7577   1.0000
   4.500   0.6169   0.03113   0.02211  -0.0495   0.7348   1.0000
   4.750   0.6537   0.03058   0.02176  -0.0486   0.7069   1.0000
   5.000   0.6925   0.02967   0.02107  -0.0474   0.6777   1.0000
   5.250   0.7323   0.02839   0.01994  -0.0457   0.6467   1.0000
   5.500   0.7635   0.02743   0.01908  -0.0433   0.6112   1.0000
   5.750   0.7947   0.02648   0.01815  -0.0408   0.5750   1.0000
   6.000   0.8220   0.02603   0.01766  -0.0385   0.5380   1.0000
   6.250   0.8483   0.02588   0.01740  -0.0364   0.5004   1.0000
   6.500   0.8707   0.02624   0.01768  -0.0342   0.4603   1.0000
   6.750   0.8914   0.02693   0.01819  -0.0320   0.4171   1.0000
   7.000   0.9094   0.02785   0.01891  -0.0296   0.3704   1.0000
   7.250   0.9275   0.02899   0.01966  -0.0273   0.3222   1.0000
   7.500   0.9439   0.03078   0.02115  -0.0252   0.2758   1.0000
   7.750   0.9598   0.03267   0.02290  -0.0233   0.2360   1.0000
   8.000   0.9777   0.03466   0.02466  -0.0217   0.2037   1.0000
   8.250   0.9926   0.03662   0.02679  -0.0198   0.1787   1.0000
   8.500   1.0122   0.03875   0.02888  -0.0186   0.1604   1.0000
   8.750   1.0293   0.04108   0.03137  -0.0171   0.1461   1.0000
   9.000   1.0505   0.04379   0.03411  -0.0163   0.1349   1.0000
   9.250   1.0577   0.04740   0.03841  -0.0141   0.1295   1.0000
   9.500   1.0792   0.05037   0.04121  -0.0137   0.1211   1.0000
   9.750   1.0755   0.05422   0.04577  -0.0110   0.1186   1.0000
  10.000   1.0705   0.05851   0.05056  -0.0087   0.1171   1.0000
  10.250   1.0607   0.06301   0.05547  -0.0066   0.1168   1.0000
  10.500   1.0452   0.06763   0.06042  -0.0047   0.1171   1.0000
  10.750   1.0236   0.07216   0.06519  -0.0028   0.1178   1.0000
  11.000   0.9994   0.07696   0.07013  -0.0019   0.1188   1.0000
  11.250   0.9758   0.08242   0.07570  -0.0023   0.1198   1.0000
  11.500   0.9583   0.08841   0.08176  -0.0037   0.1208   1.0000
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