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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 50,000
Max Cl/Cd: 40.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3510-il-50000-n5.txt
Download as CSV file: xf-hq3510-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3493   0.11244   0.10571  -0.0397   1.0000   0.0951
  -9.000  -0.3601   0.11074   0.10415  -0.0410   1.0000   0.0957
  -8.750  -0.3706   0.10882   0.10237  -0.0415   1.0000   0.0960
  -8.500  -0.3642   0.10460   0.09824  -0.0401   1.0000   0.0968
  -8.250  -0.3594   0.10117   0.09486  -0.0384   1.0000   0.0978
  -8.000  -0.3568   0.09833   0.09207  -0.0366   1.0000   0.1001
  -7.750  -0.3620   0.09383   0.08760  -0.0369   1.0000   0.0628
  -7.500  -0.3817   0.09106   0.08496  -0.0364   1.0000   0.0520
  -7.250  -0.3897   0.08864   0.08264  -0.0350   1.0000   0.0510
  -7.000  -0.3971   0.08600   0.08009  -0.0342   1.0000   0.0494
  -6.750  -0.4052   0.08298   0.07716  -0.0347   1.0000   0.0489
  -6.500  -0.4113   0.07957   0.07380  -0.0357   1.0000   0.0480
  -6.250  -0.4152   0.07584   0.07008  -0.0372   1.0000   0.0465
  -6.000  -0.4162   0.07185   0.06606  -0.0390   1.0000   0.0456
  -5.750  -0.4136   0.06779   0.06192  -0.0409   1.0000   0.0451
  -5.500  -0.4067   0.06319   0.05714  -0.0436   1.0000   0.0441
  -5.250  -0.3797   0.05762   0.05122  -0.0497   0.9951   0.0438
  -4.750  -0.3099   0.04721   0.03940  -0.0606   0.9850   0.0412
  -4.500  -0.2789   0.04328   0.03490  -0.0635   0.9799   0.0412
  -4.250  -0.2457   0.03963   0.03079  -0.0663   0.9757   0.0417
  -4.000  -0.2117   0.03655   0.02726  -0.0688   0.9718   0.0428
  -3.750  -0.1804   0.03427   0.02459  -0.0701   0.9668   0.0445
  -3.500  -0.1463   0.03253   0.02247  -0.0718   0.9623   0.0493
  -3.250  -0.1102   0.03080   0.02023  -0.0731   0.9585   0.0551
  -3.000  -0.0821   0.02945   0.01878  -0.0733   0.9529   0.0615
  -2.750  -0.0499   0.02829   0.01742  -0.0740   0.9482   0.0750
  -2.500  -0.0177   0.02732   0.01624  -0.0747   0.9435   0.0961
  -2.250   0.0121   0.02637   0.01526  -0.0756   0.9376   0.1225
  -2.000   0.0489   0.02537   0.01432  -0.0778   0.9331   0.1595
  -1.750   0.0759   0.02337   0.01429  -0.0784   0.9286   0.5512
  -1.500   0.0918   0.02331   0.01451  -0.0745   0.9213   0.7310
  -1.250   0.1052   0.02309   0.01444  -0.0700   0.9143   0.8375
  -1.000   0.1442   0.02273   0.01400  -0.0715   0.9075   1.0000
  -0.750   0.1797   0.02298   0.01386  -0.0738   0.9010   1.0000
  -0.500   0.2128   0.02323   0.01377  -0.0755   0.8935   1.0000
  -0.250   0.2468   0.02351   0.01375  -0.0773   0.8864   1.0000
   0.000   0.2803   0.02377   0.01377  -0.0789   0.8789   1.0000
   0.250   0.3111   0.02405   0.01383  -0.0800   0.8707   1.0000
   0.500   0.3474   0.02428   0.01388  -0.0819   0.8638   1.0000
   0.750   0.3752   0.02459   0.01404  -0.0824   0.8543   1.0000
   1.000   0.4151   0.02473   0.01405  -0.0847   0.8483   1.0000
   1.500   0.4707   0.02531   0.01445  -0.0853   0.8287   1.0000
   1.750   0.5081   0.02540   0.01449  -0.0870   0.8213   1.0000
   2.000   0.5367   0.02555   0.01461  -0.0871   0.8095   1.0000
   2.250   0.5689   0.02546   0.01450  -0.0874   0.7966   1.0000
   2.500   0.6021   0.02525   0.01427  -0.0876   0.7829   1.0000
   2.750   0.6343   0.02503   0.01408  -0.0877   0.7690   1.0000
   3.000   0.6647   0.02491   0.01399  -0.0876   0.7557   1.0000
   3.250   0.6939   0.02486   0.01399  -0.0873   0.7429   1.0000
   3.500   0.7230   0.02480   0.01398  -0.0871   0.7295   1.0000
   3.750   0.7518   0.02472   0.01402  -0.0867   0.7153   1.0000
   4.000   0.7804   0.02462   0.01400  -0.0862   0.7002   1.0000
   4.250   0.8094   0.02448   0.01394  -0.0857   0.6843   1.0000
   4.500   0.8395   0.02427   0.01383  -0.0853   0.6675   1.0000
   4.750   0.8628   0.02436   0.01407  -0.0840   0.6462   1.0000
   5.000   0.8922   0.02417   0.01397  -0.0834   0.6253   1.0000
   5.250   0.9162   0.02425   0.01415  -0.0822   0.5998   1.0000
   5.500   0.9418   0.02429   0.01424  -0.0811   0.5722   1.0000
   5.750   0.9678   0.02438   0.01440  -0.0801   0.5426   1.0000
   6.000   0.9920   0.02463   0.01464  -0.0789   0.5108   1.0000
   6.250   1.0152   0.02504   0.01502  -0.0777   0.4790   1.0000
   6.500   1.0374   0.02561   0.01552  -0.0765   0.4491   1.0000
   6.750   1.0587   0.02632   0.01623  -0.0753   0.4220   1.0000
   7.000   1.0796   0.02711   0.01700  -0.0742   0.3975   1.0000
   7.250   1.0999   0.02797   0.01787  -0.0730   0.3750   1.0000
   7.500   1.1199   0.02888   0.01884  -0.0719   0.3541   1.0000
   7.750   1.1395   0.02982   0.01985  -0.0708   0.3344   1.0000
   8.000   1.1589   0.03078   0.02087  -0.0697   0.3158   1.0000
   8.250   1.1768   0.03181   0.02205  -0.0684   0.2971   1.0000
   8.500   1.1941   0.03289   0.02330  -0.0670   0.2789   1.0000
   8.750   1.2108   0.03401   0.02449  -0.0656   0.2613   1.0000
   9.000   1.2242   0.03522   0.02591  -0.0639   0.2433   1.0000
   9.250   1.2357   0.03647   0.02737  -0.0619   0.2254   1.0000
   9.500   1.2428   0.03771   0.02876  -0.0594   0.2079   1.0000
   9.750   1.2463   0.03903   0.03020  -0.0566   0.1906   1.0000
  10.000   1.2451   0.04056   0.03193  -0.0537   0.1712   1.0000
  10.250   1.2402   0.04230   0.03370  -0.0509   0.1520   1.0000
  10.500   1.2346   0.04446   0.03590  -0.0487   0.1295   1.0000
  10.750   1.2277   0.04712   0.03848  -0.0469   0.1071   1.0000
  11.000   1.2194   0.05035   0.04159  -0.0457   0.0869   1.0000
  11.250   1.2118   0.05398   0.04518  -0.0447   0.0682   1.0000
  11.500   1.2033   0.05793   0.04914  -0.0441   0.0570   1.0000
  11.750   1.1929   0.06224   0.05353  -0.0440   0.0502   1.0000
  12.000   1.1864   0.06645   0.05794  -0.0439   0.0442   1.0000
  12.250   1.1775   0.07101   0.06259  -0.0444   0.0407   1.0000
  12.500   1.1693   0.07569   0.06739  -0.0451   0.0381   1.0000
  12.750   1.1635   0.08033   0.07229  -0.0458   0.0352   1.0000
  13.000   1.1563   0.08526   0.07742  -0.0471   0.0329   1.0000
  13.250   1.1487   0.09037   0.08267  -0.0488   0.0313   1.0000
  13.500   1.1411   0.09563   0.08803  -0.0506   0.0300   1.0000
  13.750   1.1345   0.10089   0.09337  -0.0524   0.0290   1.0000
  14.000   1.1286   0.10649   0.09928  -0.0545   0.0282   1.0000
  14.250   1.1216   0.11253   0.10558  -0.0570   0.0276   1.0000
  14.500   1.1134   0.11906   0.11235  -0.0600   0.0273   1.0000
  14.750   1.1040   0.12616   0.11968  -0.0637   0.0271   1.0000
  15.000   1.0928   0.13402   0.12776  -0.0680   0.0270   1.0000
  15.250   1.0807   0.14256   0.13648  -0.0730   0.0272   1.0000
  15.500   1.0681   0.15173   0.14578  -0.0784   0.0275   1.0000
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