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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 500,000
Max Cl/Cd: 92.55 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3011-il-500000-n5.txt
Download as CSV file: xf-hq3011-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3976   0.09247   0.09020  -0.0421   1.0000   0.0061
 -10.000  -0.4040   0.08748   0.08525  -0.0440   1.0000   0.0060
  -9.500  -0.5581   0.03168   0.02858  -0.0900   0.9606   0.0055
  -9.250  -0.5461   0.02707   0.02344  -0.0921   0.9492   0.0057
  -9.000  -0.5277   0.02437   0.02035  -0.0928   0.9400   0.0059
  -8.750  -0.5082   0.02226   0.01788  -0.0929   0.9310   0.0061
  -8.500  -0.4876   0.02062   0.01594  -0.0927   0.9230   0.0063
  -8.250  -0.4653   0.01922   0.01427  -0.0925   0.9160   0.0066
  -8.000  -0.4420   0.01829   0.01313  -0.0921   0.9090   0.0069
  -7.750  -0.4182   0.01737   0.01200  -0.0918   0.9028   0.0072
  -7.500  -0.3964   0.01603   0.01047  -0.0913   0.8963   0.0077
  -7.250  -0.3721   0.01526   0.00958  -0.0910   0.8901   0.0080
  -7.000  -0.3474   0.01455   0.00875  -0.0907   0.8844   0.0083
  -6.750  -0.3223   0.01392   0.00799  -0.0903   0.8782   0.0087
  -6.250  -0.2713   0.01280   0.00665  -0.0898   0.8668   0.0094
  -6.000  -0.2454   0.01233   0.00607  -0.0895   0.8611   0.0098
  -5.750  -0.2191   0.01192   0.00556  -0.0893   0.8557   0.0103
  -5.500  -0.1931   0.01143   0.00500  -0.0891   0.8497   0.0112
  -5.250  -0.1665   0.01105   0.00454  -0.0889   0.8444   0.0123
  -5.000  -0.1397   0.01072   0.00415  -0.0887   0.8384   0.0133
  -4.750  -0.1127   0.01042   0.00379  -0.0886   0.8326   0.0151
  -4.500  -0.0858   0.01011   0.00350  -0.0884   0.8270   0.0219
  -4.250  -0.0584   0.00992   0.00328  -0.0884   0.8209   0.0289
  -4.000  -0.0311   0.00972   0.00306  -0.0883   0.8155   0.0349
  -3.750  -0.0035   0.00957   0.00288  -0.0883   0.8091   0.0393
  -3.500   0.0239   0.00938   0.00269  -0.0882   0.8031   0.0467
  -3.250   0.0515   0.00923   0.00252  -0.0882   0.7968   0.0554
  -3.000   0.0789   0.00905   0.00235  -0.0881   0.7901   0.0677
  -2.750   0.1064   0.00887   0.00219  -0.0881   0.7832   0.0841
  -2.500   0.1337   0.00868   0.00203  -0.0881   0.7755   0.1085
  -2.250   0.1609   0.00842   0.00189  -0.0880   0.7676   0.1542
  -2.000   0.1877   0.00810   0.00175  -0.0880   0.7600   0.2266
  -1.750   0.2145   0.00772   0.00162  -0.0881   0.7528   0.3171
  -1.500   0.2405   0.00724   0.00156  -0.0881   0.7459   0.4609
  -1.250   0.2678   0.00712   0.00156  -0.0880   0.7391   0.5199
  -1.000   0.2954   0.00708   0.00156  -0.0878   0.7316   0.5526
  -0.750   0.3228   0.00705   0.00156  -0.0877   0.7219   0.5845
  -0.500   0.3496   0.00702   0.00158  -0.0874   0.7108   0.6176
  -0.250   0.3768   0.00703   0.00157  -0.0872   0.6997   0.6361
   0.000   0.4041   0.00705   0.00157  -0.0870   0.6893   0.6491
   0.250   0.4318   0.00706   0.00158  -0.0869   0.6803   0.6592
   0.500   0.4593   0.00710   0.00158  -0.0868   0.6711   0.6677
   0.750   0.4868   0.00713   0.00160  -0.0867   0.6610   0.6754
   1.000   0.5142   0.00717   0.00163  -0.0866   0.6500   0.6840
   1.250   0.5412   0.00722   0.00166  -0.0864   0.6365   0.6935
   1.500   0.5677   0.00728   0.00169  -0.0861   0.6195   0.7040
   1.750   0.5941   0.00736   0.00175  -0.0858   0.6026   0.7165
   2.000   0.6203   0.00742   0.00182  -0.0854   0.5856   0.7312
   2.250   0.6459   0.00750   0.00190  -0.0849   0.5659   0.7500
   2.500   0.6707   0.00761   0.00202  -0.0843   0.5449   0.7745
   2.750   0.6950   0.00775   0.00216  -0.0835   0.5206   0.8036
   3.000   0.7186   0.00794   0.00230  -0.0827   0.4927   0.8321
   3.250   0.7422   0.00818   0.00246  -0.0819   0.4641   0.8541
   3.500   0.7656   0.00842   0.00262  -0.0810   0.4359   0.8719
   3.750   0.7886   0.00866   0.00280  -0.0801   0.4087   0.8892
   4.000   0.8111   0.00887   0.00297  -0.0791   0.3821   0.9120
   4.250   0.8441   0.00912   0.00317  -0.0804   0.3524   1.0000
   4.500   0.8682   0.00947   0.00340  -0.0799   0.3250   1.0000
   5.000   0.9165   0.01015   0.00390  -0.0789   0.2820   1.0000
   5.250   0.9407   0.01048   0.00416  -0.0784   0.2641   1.0000
   5.500   0.9646   0.01083   0.00443  -0.0779   0.2464   1.0000
   5.750   0.9884   0.01117   0.00472  -0.0773   0.2290   1.0000
   6.000   1.0112   0.01158   0.00503  -0.0767   0.2051   1.0000
   6.250   1.0328   0.01208   0.00538  -0.0758   0.1774   1.0000
   6.500   1.0544   0.01258   0.00575  -0.0750   0.1538   1.0000
   6.750   1.0757   0.01307   0.00615  -0.0741   0.1332   1.0000
   7.000   1.0963   0.01362   0.00657  -0.0731   0.1097   1.0000
   7.250   1.1165   0.01418   0.00701  -0.0721   0.0893   1.0000
   7.500   1.1371   0.01469   0.00746  -0.0711   0.0747   1.0000
   7.750   1.1568   0.01525   0.00795  -0.0700   0.0605   1.0000
   8.000   1.1756   0.01585   0.00848  -0.0687   0.0475   1.0000
   8.250   1.1929   0.01654   0.00910  -0.0672   0.0336   1.0000
   8.500   1.2103   0.01718   0.00969  -0.0658   0.0242   1.0000
   8.750   1.2248   0.01791   0.01036  -0.0638   0.0145   1.0000
   9.000   1.2371   0.01872   0.01113  -0.0615   0.0057   1.0000
   9.250   1.2511   0.01942   0.01185  -0.0595   0.0047   1.0000
   9.500   1.2657   0.02008   0.01256  -0.0576   0.0040   1.0000
   9.750   1.2806   0.02072   0.01328  -0.0559   0.0039   1.0000
  10.000   1.2945   0.02144   0.01411  -0.0540   0.0037   1.0000
  10.250   1.3076   0.02223   0.01499  -0.0522   0.0035   1.0000
  10.500   1.3199   0.02308   0.01593  -0.0504   0.0033   1.0000
  10.750   1.3312   0.02403   0.01698  -0.0485   0.0032   1.0000
  11.000   1.3415   0.02508   0.01813  -0.0466   0.0031   1.0000
  11.250   1.3505   0.02624   0.01940  -0.0447   0.0030   1.0000
  11.500   1.3592   0.02747   0.02073  -0.0429   0.0029   1.0000
  11.750   1.3659   0.02888   0.02225  -0.0411   0.0028   1.0000
  12.000   1.3697   0.03058   0.02408  -0.0392   0.0027   1.0000
  12.250   1.3731   0.03236   0.02598  -0.0374   0.0027   1.0000
  12.500   1.3746   0.03438   0.02814  -0.0358   0.0026   1.0000
  12.750   1.3746   0.03662   0.03051  -0.0343   0.0026   1.0000
  13.000   1.3762   0.03881   0.03281  -0.0331   0.0025   1.0000
  13.250   1.3803   0.04083   0.03495  -0.0323   0.0025   1.0000
  13.500   1.3823   0.04315   0.03739  -0.0316   0.0024   1.0000
  13.750   1.3837   0.04564   0.03999  -0.0311   0.0024   1.0000
  14.000   1.3815   0.04862   0.04310  -0.0307   0.0023   1.0000
  14.250   1.3783   0.05187   0.04649  -0.0307   0.0023   1.0000
  14.500   1.3746   0.05536   0.05011  -0.0310   0.0023   1.0000
  14.750   1.3696   0.05921   0.05410  -0.0315   0.0022   1.0000
  15.000   1.3628   0.06352   0.05855  -0.0325   0.0022   1.0000
  15.250   1.3541   0.06837   0.06355  -0.0340   0.0022   1.0000
  15.500   1.3457   0.07342   0.06874  -0.0357   0.0022   1.0000
  15.750   1.3353   0.07906   0.07453  -0.0380   0.0022   1.0000
  16.000   1.3263   0.08471   0.08032  -0.0405   0.0021   1.0000
  16.250   1.3123   0.09146   0.08722  -0.0436   0.0021   1.0000
  16.500   1.3007   0.09803   0.09393  -0.0468   0.0021   1.0000
  16.750   1.2872   0.10512   0.10118  -0.0504   0.0021   1.0000
  17.000   1.2738   0.11239   0.10858  -0.0541   0.0021   1.0000
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