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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.72 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3011-il-1000000.txt
Download as CSV file: xf-hq3011-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5097   0.03517   0.03305  -0.0892   0.9766   0.0071
  -9.000  -0.4947   0.02940   0.02681  -0.0945   0.9678   0.0070
  -8.750  -0.4892   0.02383   0.02061  -0.0957   0.9529   0.0071
  -8.500  -0.4821   0.01954   0.01571  -0.0947   0.9400   0.0073
  -8.250  -0.4643   0.01763   0.01352  -0.0939   0.9305   0.0074
  -8.000  -0.4433   0.01629   0.01199  -0.0932   0.9229   0.0076
  -7.750  -0.4209   0.01524   0.01076  -0.0927   0.9157   0.0078
  -7.500  -0.3975   0.01430   0.00966  -0.0922   0.9093   0.0079
  -7.250  -0.3734   0.01353   0.00877  -0.0917   0.9028   0.0081
  -7.000  -0.3486   0.01286   0.00798  -0.0913   0.8970   0.0084
  -6.750  -0.3232   0.01234   0.00737  -0.0910   0.8909   0.0088
  -6.500  -0.2979   0.01176   0.00668  -0.0906   0.8852   0.0092
  -6.250  -0.2723   0.01117   0.00600  -0.0903   0.8794   0.0095
  -6.000  -0.2464   0.01067   0.00539  -0.0899   0.8736   0.0098
  -5.750  -0.2208   0.01007   0.00467  -0.0896   0.8682   0.0105
  -5.500  -0.1949   0.00950   0.00403  -0.0893   0.8622   0.0114
  -5.250  -0.1681   0.00918   0.00364  -0.0891   0.8567   0.0124
  -5.000  -0.1409   0.00890   0.00331  -0.0890   0.8511   0.0135
  -4.750  -0.1137   0.00858   0.00293  -0.0888   0.8452   0.0157
  -4.500  -0.0866   0.00829   0.00268  -0.0887   0.8397   0.0248
  -4.250  -0.0590   0.00811   0.00254  -0.0887   0.8335   0.0344
  -4.000  -0.0313   0.00799   0.00237  -0.0886   0.8277   0.0390
  -3.750  -0.0035   0.00783   0.00222  -0.0886   0.8213   0.0443
  -3.500   0.0243   0.00775   0.00209  -0.0886   0.8145   0.0473
  -3.250   0.0519   0.00755   0.00191  -0.0885   0.8073   0.0572
  -3.000   0.0795   0.00740   0.00176  -0.0885   0.7999   0.0696
  -2.750   0.1071   0.00719   0.00162  -0.0885   0.7930   0.0946
  -2.500   0.1342   0.00687   0.00147  -0.0885   0.7862   0.1551
  -2.250   0.1610   0.00642   0.00134  -0.0886   0.7798   0.2609
  -2.000   0.1868   0.00580   0.00120  -0.0886   0.7731   0.4232
  -1.750   0.2140   0.00559   0.00118  -0.0885   0.7661   0.5031
  -1.500   0.2417   0.00554   0.00115  -0.0885   0.7576   0.5367
  -1.250   0.2696   0.00550   0.00113  -0.0884   0.7486   0.5599
  -1.000   0.2974   0.00551   0.00112  -0.0883   0.7400   0.5791
  -0.750   0.3254   0.00549   0.00112  -0.0883   0.7315   0.5990
  -0.500   0.3534   0.00550   0.00111  -0.0883   0.7243   0.6125
  -0.250   0.3814   0.00549   0.00112  -0.0882   0.7163   0.6287
   0.000   0.4092   0.00549   0.00114  -0.0881   0.7087   0.6487
   0.250   0.4370   0.00551   0.00115  -0.0881   0.7001   0.6607
   0.500   0.4648   0.00551   0.00116  -0.0880   0.6905   0.6727
   0.750   0.4923   0.00554   0.00117  -0.0879   0.6796   0.6843
   1.000   0.5198   0.00558   0.00119  -0.0878   0.6689   0.6951
   1.250   0.5475   0.00559   0.00122  -0.0878   0.6585   0.7058
   1.500   0.5750   0.00561   0.00125  -0.0877   0.6478   0.7182
   1.750   0.6022   0.00563   0.00130  -0.0875   0.6358   0.7342
   2.000   0.6290   0.00566   0.00136  -0.0873   0.6230   0.7559
   2.250   0.6552   0.00568   0.00144  -0.0869   0.6078   0.7866
   2.500   0.6809   0.00573   0.00153  -0.0864   0.5903   0.8223
   3.000   0.7318   0.00598   0.00172  -0.0854   0.5469   0.8679
   3.250   0.7563   0.00614   0.00182  -0.0847   0.5202   0.8848
   3.500   0.7798   0.00629   0.00193  -0.0838   0.4911   0.9034
   3.750   0.8032   0.00644   0.00207  -0.0829   0.4607   0.9428
   4.500   0.8859   0.00735   0.00260  -0.0834   0.3676   1.0000
   4.750   0.9102   0.00769   0.00280  -0.0829   0.3361   1.0000
   5.000   0.9344   0.00804   0.00302  -0.0824   0.3071   1.0000
   5.250   0.9584   0.00840   0.00325  -0.0819   0.2817   1.0000
   5.500   0.9829   0.00872   0.00349  -0.0814   0.2599   1.0000
   5.750   1.0069   0.00906   0.00373  -0.0809   0.2376   1.0000
   6.000   1.0302   0.00946   0.00399  -0.0802   0.2117   1.0000
   6.250   1.0533   0.00986   0.00427  -0.0796   0.1869   1.0000
   6.500   1.0765   0.01024   0.00457  -0.0789   0.1668   1.0000
   6.750   1.1000   0.01060   0.00485  -0.0783   0.1509   1.0000
   7.000   1.1230   0.01097   0.00515  -0.0777   0.1352   1.0000
   7.250   1.1452   0.01140   0.00549  -0.0769   0.1180   1.0000
   7.500   1.1669   0.01185   0.00585  -0.0760   0.1002   1.0000
   7.750   1.1869   0.01243   0.00630  -0.0749   0.0790   1.0000
   8.000   1.2075   0.01294   0.00673  -0.0739   0.0636   1.0000
   8.250   1.2266   0.01354   0.00722  -0.0726   0.0473   1.0000
   8.500   1.2462   0.01408   0.00769  -0.0714   0.0370   1.0000
   8.750   1.2644   0.01470   0.00823  -0.0700   0.0261   1.0000
   9.000   1.2817   0.01536   0.00882  -0.0685   0.0162   1.0000
   9.250   1.2960   0.01618   0.00959  -0.0665   0.0067   1.0000
   9.500   1.3115   0.01677   0.01019  -0.0645   0.0052   1.0000
   9.750   1.3255   0.01738   0.01086  -0.0623   0.0045   1.0000
  10.000   1.3395   0.01800   0.01155  -0.0602   0.0041   1.0000
  10.250   1.3527   0.01868   0.01230  -0.0580   0.0039   1.0000
  10.500   1.3665   0.01932   0.01301  -0.0560   0.0039   1.0000
  10.750   1.3787   0.02008   0.01384  -0.0539   0.0038   1.0000
  11.000   1.3897   0.02095   0.01479  -0.0517   0.0036   1.0000
  11.250   1.4013   0.02178   0.01571  -0.0497   0.0036   1.0000
  11.500   1.4112   0.02275   0.01676  -0.0476   0.0035   1.0000
  11.750   1.4214   0.02371   0.01779  -0.0457   0.0034   1.0000
  12.000   1.4279   0.02498   0.01916  -0.0435   0.0033   1.0000
  12.250   1.4362   0.02615   0.02040  -0.0417   0.0032   1.0000
  12.500   1.4414   0.02759   0.02195  -0.0397   0.0032   1.0000
  12.750   1.4473   0.02904   0.02348  -0.0379   0.0031   1.0000
  13.000   1.4514   0.03068   0.02522  -0.0362   0.0031   1.0000
  13.250   1.4513   0.03275   0.02741  -0.0343   0.0031   1.0000
  13.500   1.4516   0.03488   0.02965  -0.0328   0.0030   1.0000
  13.750   1.4535   0.03696   0.03183  -0.0316   0.0030   1.0000
  14.000   1.4530   0.03938   0.03437  -0.0305   0.0030   1.0000
  14.250   1.4502   0.04214   0.03724  -0.0297   0.0029   1.0000
  14.500   1.4470   0.04509   0.04031  -0.0291   0.0029   1.0000
  14.750   1.4405   0.04859   0.04393  -0.0288   0.0029   1.0000
  15.000   1.4353   0.05212   0.04758  -0.0289   0.0029   1.0000
  15.250   1.4292   0.05600   0.05158  -0.0294   0.0028   1.0000
  15.500   1.4194   0.06058   0.05629  -0.0303   0.0028   1.0000
  15.750   1.4116   0.06517   0.06101  -0.0315   0.0028   1.0000
  16.000   1.3992   0.07070   0.06667  -0.0333   0.0028   1.0000
  16.250   1.3899   0.07601   0.07212  -0.0353   0.0028   1.0000
  16.500   1.3777   0.08207   0.07831  -0.0379   0.0028   1.0000
  16.750   1.3676   0.08802   0.08439  -0.0406   0.0028   1.0000
  17.000   1.3510   0.09531   0.09182  -0.0441   0.0027   1.0000
  17.250   1.3401   0.10181   0.09844  -0.0473   0.0028   1.0000
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