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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 200,000
Max Cl/Cd: 81.81 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3011-il-200000.txt
Download as CSV file: xf-hq3011-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3129   0.09116   0.08808  -0.0466   1.0000   0.0472
  -9.250  -0.3262   0.08859   0.08557  -0.0455   1.0000   0.0473
  -9.000  -0.3355   0.08371   0.08077  -0.0425   1.0000   0.0481
  -8.750  -0.3415   0.08177   0.07889  -0.0392   1.0000   0.0486
  -8.500  -0.3481   0.08015   0.07731  -0.0360   1.0000   0.0493
  -8.250  -0.3580   0.07821   0.07543  -0.0338   0.9999   0.0497
  -8.000  -0.3470   0.07352   0.07074  -0.0369   0.9968   0.0511
  -7.750  -0.4639   0.07696   0.07377  -0.0513   0.9946   0.0473
  -7.500  -0.4547   0.06982   0.06680  -0.0521   0.9920   0.0488
  -7.250  -0.4349   0.06633   0.06331  -0.0545   0.9875   0.0502
  -7.000  -0.4120   0.06140   0.05827  -0.0609   0.9830   0.0520
  -6.750  -0.3948   0.05638   0.05308  -0.0662   0.9753   0.0543
  -6.500  -0.3644   0.05244   0.04817  -0.0749   0.9678   0.0601
  -6.250  -0.3526   0.04474   0.04057  -0.0771   0.9618   0.0621
  -6.000  -0.3257   0.03298   0.02779  -0.0794   0.9575   0.0333
  -5.750  -0.2952   0.02816   0.02234  -0.0814   0.9540   0.0317
  -5.500  -0.2703   0.02530   0.01900  -0.0813   0.9475   0.0319
  -5.250  -0.2338   0.02374   0.01699  -0.0830   0.9442   0.0350
  -5.000  -0.1962   0.02128   0.01412  -0.0848   0.9422   0.0365
  -4.750  -0.1678   0.01952   0.01229  -0.0852   0.9372   0.0398
  -4.500  -0.1347   0.01867   0.01130  -0.0861   0.9326   0.0464
  -4.250  -0.0974   0.01757   0.01014  -0.0881   0.9299   0.0595
  -4.000  -0.0596   0.01660   0.00915  -0.0902   0.9276   0.0744
  -3.750  -0.0338   0.01622   0.00875  -0.0900   0.9207   0.0874
  -3.500  -0.0013   0.01540   0.00799  -0.0911   0.9165   0.0999
  -3.250   0.0342   0.01459   0.00727  -0.0927   0.9136   0.1206
  -3.000   0.0582   0.01387   0.00682  -0.0923   0.9065   0.1746
  -2.750   0.0818   0.01233   0.00671  -0.0922   0.9015   0.5425
  -2.500   0.1148   0.01221   0.00666  -0.0926   0.8983   0.6169
  -2.250   0.1369   0.01227   0.00671  -0.0912   0.8898   0.6509
  -2.000   0.1681   0.01216   0.00659  -0.0913   0.8856   0.6819
  -1.750   0.1924   0.01215   0.00660  -0.0902   0.8783   0.7063
  -1.500   0.2203   0.01203   0.00650  -0.0897   0.8727   0.7301
  -1.250   0.2458   0.01199   0.00650  -0.0885   0.8668   0.7589
  -1.000   0.2680   0.01200   0.00658  -0.0866   0.8595   0.7878
  -0.750   0.2963   0.01192   0.00648  -0.0859   0.8553   0.8085
  -0.500   0.3180   0.01197   0.00654  -0.0845   0.8464   0.8248
  -0.250   0.3471   0.01183   0.00636  -0.0842   0.8417   0.8386
   0.000   0.3703   0.01182   0.00636  -0.0832   0.8334   0.8535
   0.250   0.3985   0.01161   0.00610  -0.0828   0.8275   0.8699
   0.500   0.4207   0.01142   0.00594  -0.0812   0.8175   0.8883
   0.750   0.4467   0.01113   0.00566  -0.0801   0.8092   0.9103
   1.000   0.4785   0.01091   0.00545  -0.0804   0.8008   0.9358
   1.250   0.5217   0.01076   0.00530  -0.0835   0.7930   0.9657
   1.500   0.5685   0.01059   0.00508  -0.0875   0.7854   1.0000
   1.750   0.5929   0.01062   0.00506  -0.0872   0.7753   1.0000
   2.000   0.6206   0.01060   0.00496  -0.0871   0.7660   1.0000
   2.250   0.6487   0.01056   0.00485  -0.0870   0.7559   1.0000
   2.500   0.6749   0.01056   0.00482  -0.0866   0.7436   1.0000
   2.750   0.7014   0.01058   0.00482  -0.0862   0.7312   1.0000
   3.000   0.7280   0.01061   0.00482  -0.0858   0.7186   1.0000
   3.250   0.7546   0.01064   0.00482  -0.0854   0.7053   1.0000
   3.500   0.7809   0.01068   0.00484  -0.0850   0.6911   1.0000
   3.750   0.8069   0.01074   0.00489  -0.0844   0.6755   1.0000
   4.000   0.8327   0.01081   0.00493  -0.0839   0.6584   1.0000
   4.250   0.8582   0.01090   0.00498  -0.0832   0.6395   1.0000
   4.500   0.8827   0.01102   0.00509  -0.0824   0.6171   1.0000
   4.750   0.9068   0.01117   0.00521  -0.0816   0.5925   1.0000
   5.000   0.9302   0.01137   0.00534  -0.0806   0.5641   1.0000
   5.250   0.9526   0.01166   0.00552  -0.0795   0.5314   1.0000
   5.500   0.9738   0.01204   0.00577  -0.0782   0.4954   1.0000
   5.750   0.9939   0.01251   0.00608  -0.0768   0.4576   1.0000
   6.000   1.0133   0.01306   0.00646  -0.0754   0.4206   1.0000
   6.250   1.0321   0.01367   0.00690  -0.0739   0.3855   1.0000
   6.500   1.0507   0.01429   0.00738  -0.0725   0.3535   1.0000
   6.750   1.0693   0.01491   0.00790  -0.0711   0.3241   1.0000
   7.000   1.0874   0.01557   0.00844  -0.0696   0.2982   1.0000
   7.250   1.1062   0.01619   0.00900  -0.0683   0.2746   1.0000
   7.500   1.1240   0.01688   0.00959  -0.0669   0.2544   1.0000
   7.750   1.1428   0.01746   0.01018  -0.0656   0.2343   1.0000
   8.000   1.1605   0.01809   0.01080  -0.0641   0.2158   1.0000
   8.250   1.1768   0.01878   0.01144  -0.0625   0.1985   1.0000
   8.500   1.1936   0.01942   0.01209  -0.0610   0.1802   1.0000
   8.750   1.2079   0.02011   0.01276  -0.0591   0.1615   1.0000
   9.000   1.2191   0.02092   0.01348  -0.0568   0.1432   1.0000
   9.250   1.2326   0.02166   0.01422  -0.0549   0.1239   1.0000
   9.500   1.2438   0.02256   0.01507  -0.0528   0.1070   1.0000
   9.750   1.2540   0.02358   0.01606  -0.0506   0.0927   1.0000
  10.000   1.2643   0.02463   0.01712  -0.0486   0.0812   1.0000
  10.250   1.2744   0.02573   0.01826  -0.0466   0.0723   1.0000
  10.500   1.2806   0.02712   0.01962  -0.0443   0.0655   1.0000
  10.750   1.2927   0.02813   0.02074  -0.0428   0.0578   1.0000
  11.000   1.3013   0.02942   0.02209  -0.0410   0.0500   1.0000
  11.250   1.3041   0.03119   0.02384  -0.0390   0.0431   1.0000
  11.500   1.3063   0.03313   0.02583  -0.0370   0.0333   1.0000
  11.750   1.3090   0.03514   0.02792  -0.0352   0.0263   1.0000
  12.000   1.3067   0.03766   0.03053  -0.0333   0.0216   1.0000
  12.250   1.3071   0.03998   0.03299  -0.0319   0.0198   1.0000
  12.500   1.3015   0.04299   0.03608  -0.0305   0.0183   1.0000
  12.750   1.2949   0.04630   0.03950  -0.0292   0.0176   1.0000
  13.000   1.2958   0.04898   0.04235  -0.0284   0.0169   1.0000
  13.250   1.2952   0.05192   0.04546  -0.0277   0.0160   1.0000
  13.500   1.2938   0.05504   0.04874  -0.0273   0.0154   1.0000
  13.750   1.2925   0.05827   0.05212  -0.0270   0.0151   1.0000
  14.000   1.2903   0.06170   0.05571  -0.0270   0.0147   1.0000
  14.250   1.2875   0.06537   0.05952  -0.0272   0.0144   1.0000
  14.500   1.2839   0.06923   0.06355  -0.0277   0.0141   1.0000
  14.750   1.2790   0.07343   0.06791  -0.0285   0.0138   1.0000
  15.000   1.2737   0.07787   0.07252  -0.0295   0.0137   1.0000
  15.250   1.2668   0.08267   0.07750  -0.0309   0.0136   1.0000
  15.500   1.2583   0.08792   0.08293  -0.0328   0.0134   1.0000
  15.750   1.2486   0.09360   0.08880  -0.0351   0.0134   1.0000
  16.000   1.2367   0.09992   0.09535  -0.0380   0.0134   1.0000
  16.250   1.2233   0.10675   0.10239  -0.0415   0.0134   1.0000
  16.500   1.2075   0.11446   0.11032  -0.0458   0.0135   1.0000
  16.750   1.1886   0.12327   0.11939  -0.0511   0.0137   1.0000
  17.000   1.1667   0.13325   0.12961  -0.0574   0.0139   1.0000
  17.250   1.1407   0.14494   0.14155  -0.0650   0.0142   1.0000
  17.500   1.1015   0.16151   0.15837  -0.0759   0.0150   1.0000
  17.750   1.0375   0.18922   0.18614  -0.0923   0.0169   1.0000
  18.000   1.0232   0.20104   0.19790  -0.0983   0.0175   1.0000
  18.250   1.0036   0.22082   0.21755  -0.1068   0.0224   1.0000
  18.500   1.0096   0.22494   0.22166  -0.1087   0.0237   1.0000
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