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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 200,000
Max Cl/Cd: 77.31 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3010-il-200000-n5.txt
Download as CSV file: xf-hq3010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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  -0.3701   0.09569   0.09213  -0.0395   1.0000   0.0129
  -9.250  -0.3699   0.09240   0.08887  -0.0401   1.0000   0.0126
  -9.000  -0.3715   0.08897   0.08550  -0.0408   1.0000   0.0124
  -8.750  -0.3745   0.08558   0.08217  -0.0414   1.0000   0.0122
  -8.500  -0.3792   0.08250   0.07917  -0.0416   1.0000   0.0120
  -8.250  -0.3904   0.07939   0.07615  -0.0411   1.0000   0.0120
  -8.000  -0.4003   0.07625   0.07308  -0.0414   0.9981   0.0118
  -7.750  -0.3899   0.06950   0.06635  -0.0508   0.9873   0.0116
  -7.500  -0.3741   0.05981   0.05656  -0.0661   0.9767   0.0112
  -7.250  -0.3584   0.05125   0.04776  -0.0762   0.9685   0.0110
  -7.000  -0.3406   0.04352   0.03967  -0.0830   0.9609   0.0108
  -6.750  -0.3227   0.03643   0.03209  -0.0869   0.9532   0.0109
  -6.500  -0.3001   0.03058   0.02563  -0.0894   0.9470   0.0115
  -6.250  -0.2749   0.02654   0.02092  -0.0906   0.9414   0.0130
  -6.000  -0.2495   0.02358   0.01742  -0.0911   0.9353   0.0132
  -5.750  -0.2204   0.02097   0.01433  -0.0919   0.9314   0.0135
  -5.500  -0.1955   0.01893   0.01200  -0.0917   0.9252   0.0141
  -5.250  -0.1672   0.01767   0.01056  -0.0921   0.9203   0.0149
  -5.000  -0.1375   0.01665   0.00940  -0.0925   0.9163   0.0160
  -4.750  -0.1115   0.01599   0.00860  -0.0923   0.9098   0.0179
  -4.500  -0.0827   0.01531   0.00778  -0.0924   0.9051   0.0199
  -4.250  -0.0563   0.01438   0.00680  -0.0923   0.8995   0.0223
  -4.000  -0.0292   0.01381   0.00614  -0.0922   0.8936   0.0265
  -3.750  -0.0005   0.01322   0.00550  -0.0923   0.8892   0.0359
  -3.500   0.0253   0.01291   0.00513  -0.0920   0.8821   0.0465
  -3.250   0.0534   0.01263   0.00486  -0.0921   0.8768   0.0640
  -3.000   0.0802   0.01234   0.00456  -0.0920   0.8706   0.0811
  -2.750   0.1073   0.01197   0.00423  -0.0919   0.8645   0.1032
  -2.500   0.1343   0.01150   0.00393  -0.0920   0.8589   0.1638
  -2.250   0.1594   0.01078   0.00370  -0.0920   0.8519   0.3116
  -2.000   0.1845   0.01015   0.00366  -0.0916   0.8465   0.5012
  -1.750   0.2093   0.00998   0.00372  -0.0908   0.8388   0.5856
  -1.500   0.2361   0.00990   0.00367  -0.0903   0.8329   0.6363
  -1.250   0.2611   0.00988   0.00371  -0.0894   0.8244   0.6776
  -1.000   0.2864   0.00984   0.00373  -0.0884   0.8172   0.7188
  -0.750   0.3119   0.00981   0.00371  -0.0876   0.8087   0.7401
  -0.500   0.3391   0.00978   0.00362  -0.0873   0.8011   0.7513
  -0.250   0.3666   0.00976   0.00354  -0.0871   0.7936   0.7611
   0.000   0.3934   0.00973   0.00350  -0.0867   0.7858   0.7704
   0.250   0.4208   0.00970   0.00341  -0.0865   0.7781   0.7804
   0.500   0.4473   0.00967   0.00336  -0.0860   0.7668   0.7913
   0.750   0.4738   0.00964   0.00330  -0.0855   0.7546   0.8025
   1.000   0.5001   0.00961   0.00326  -0.0850   0.7435   0.8145
   1.250   0.5265   0.00959   0.00324  -0.0845   0.7340   0.8278
   1.500   0.5526   0.00958   0.00324  -0.0840   0.7233   0.8431
   1.750   0.5786   0.00956   0.00324  -0.0834   0.7117   0.8612
   2.000   0.6050   0.00952   0.00325  -0.0829   0.6987   0.8860
   2.250   0.6369   0.00947   0.00323  -0.0835   0.6830   0.9293
   2.500   0.6692   0.00952   0.00322  -0.0845   0.6659   1.0000
   2.750   0.6959   0.00965   0.00329  -0.0843   0.6486   1.0000
   3.000   0.7224   0.00979   0.00340  -0.0840   0.6304   1.0000
   3.250   0.7485   0.00995   0.00349  -0.0837   0.6099   1.0000
   3.500   0.7742   0.01014   0.00361  -0.0833   0.5859   1.0000
   3.750   0.7991   0.01037   0.00374  -0.0827   0.5580   1.0000
   4.000   0.8233   0.01065   0.00393  -0.0820   0.5270   1.0000
   4.250   0.8468   0.01098   0.00413  -0.0812   0.4930   1.0000
   4.500   0.8695   0.01138   0.00438  -0.0804   0.4583   1.0000
   4.750   0.8919   0.01182   0.00467  -0.0795   0.4243   1.0000
   5.000   0.9142   0.01228   0.00503  -0.0786   0.3914   1.0000
   5.250   0.9362   0.01277   0.00540  -0.0778   0.3595   1.0000
   5.750   0.9794   0.01380   0.00621  -0.0760   0.3007   1.0000
   6.000   1.0008   0.01434   0.00666  -0.0751   0.2743   1.0000
   6.250   1.0223   0.01487   0.00716  -0.0742   0.2496   1.0000
   6.500   1.0433   0.01543   0.00765  -0.0733   0.2246   1.0000
   6.750   1.0639   0.01602   0.00816  -0.0723   0.2003   1.0000
   7.000   1.0835   0.01669   0.00870  -0.0713   0.1726   1.0000
   7.250   1.1025   0.01740   0.00928  -0.0702   0.1445   1.0000
   7.500   1.1210   0.01816   0.00989  -0.0690   0.1164   1.0000
   7.750   1.1394   0.01891   0.01054  -0.0678   0.0942   1.0000
   8.000   1.1582   0.01961   0.01126  -0.0667   0.0783   1.0000
   8.250   1.1763   0.02035   0.01199  -0.0654   0.0649   1.0000
   8.500   1.1931   0.02118   0.01279  -0.0640   0.0513   1.0000
   8.750   1.2081   0.02214   0.01368  -0.0624   0.0378   1.0000
   9.000   1.2225   0.02303   0.01459  -0.0606   0.0282   1.0000
   9.250   1.2338   0.02411   0.01562  -0.0584   0.0177   1.0000
   9.500   1.2445   0.02523   0.01676  -0.0562   0.0106   1.0000
   9.750   1.2560   0.02629   0.01790  -0.0542   0.0084   1.0000
  10.000   1.2658   0.02750   0.01924  -0.0520   0.0072   1.0000
  10.250   1.2756   0.02872   0.02060  -0.0499   0.0066   1.0000
  10.500   1.2845   0.03001   0.02205  -0.0479   0.0062   1.0000
  10.750   1.2922   0.03142   0.02362  -0.0460   0.0059   1.0000
  11.000   1.2984   0.03298   0.02534  -0.0440   0.0056   1.0000
  11.250   1.3035   0.03466   0.02719  -0.0422   0.0055   1.0000
  11.500   1.3066   0.03657   0.02927  -0.0404   0.0053   1.0000
  11.750   1.3086   0.03864   0.03150  -0.0388   0.0052   1.0000
  12.000   1.3083   0.04102   0.03406  -0.0373   0.0051   1.0000
  12.250   1.3066   0.04362   0.03683  -0.0360   0.0050   1.0000
  12.500   1.3033   0.04654   0.03992  -0.0350   0.0049   1.0000
  12.750   1.2994   0.04967   0.04322  -0.0344   0.0049   1.0000
  13.000   1.2936   0.05318   0.04691  -0.0341   0.0048   1.0000
  13.250   1.2862   0.05709   0.05100  -0.0341   0.0048   1.0000
  13.500   1.2787   0.06121   0.05531  -0.0346   0.0048   1.0000
  13.750   1.2695   0.06581   0.06007  -0.0355   0.0047   1.0000
  14.000   1.2616   0.07047   0.06491  -0.0367   0.0047   1.0000
  14.250   1.2528   0.07554   0.07021  -0.0384   0.0047   1.0000
  14.500   1.2435   0.08098   0.07584  -0.0405   0.0047   1.0000
  14.750   1.2331   0.08687   0.08192  -0.0431   0.0047   1.0000
  15.000   1.2217   0.09327   0.08850  -0.0461   0.0047   1.0000
  15.250   1.2104   0.09991   0.09532  -0.0495   0.0047   1.0000
  15.500   1.1987   0.10687   0.10245  -0.0532   0.0047   1.0000
  15.750   1.1866   0.11414   0.10989  -0.0572   0.0047   1.0000
  16.000   1.1743   0.12174   0.11765  -0.0615   0.0047   1.0000
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