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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 100,000
Max Cl/Cd: 52.73 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2010-il-100000-n5.txt
Download as CSV file: xf-hq2010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4660   0.09253   0.08754  -0.0320   1.0000   0.0212
  -9.500  -0.4686   0.08758   0.08266  -0.0345   1.0000   0.0213
  -9.250  -0.4729   0.08225   0.07739  -0.0375   1.0000   0.0213
  -9.000  -0.4789   0.07645   0.07166  -0.0412   1.0000   0.0213
  -8.750  -0.4877   0.07014   0.06541  -0.0459   1.0000   0.0211
  -8.500  -0.5004   0.06554   0.06085  -0.0486   1.0000   0.0205
  -8.250  -0.5149   0.06083   0.05609  -0.0505   1.0000   0.0204
  -8.000  -0.5269   0.05625   0.05138  -0.0511   1.0000   0.0205
  -7.750  -0.5350   0.05219   0.04716  -0.0506   1.0000   0.0205
  -7.500  -0.5413   0.04811   0.04281  -0.0495   1.0000   0.0209
  -7.250  -0.5441   0.04442   0.03879  -0.0477   1.0000   0.0213
  -7.000  -0.5434   0.04107   0.03503  -0.0457   1.0000   0.0218
  -6.750  -0.5389   0.03797   0.03149  -0.0437   1.0000   0.0220
  -6.500  -0.5314   0.03482   0.02793  -0.0419   1.0000   0.0223
  -6.250  -0.5094   0.03116   0.02383  -0.0427   0.9964   0.0230
  -6.000  -0.4796   0.02856   0.02086  -0.0444   0.9913   0.0241
  -5.750  -0.4478   0.02641   0.01831  -0.0458   0.9863   0.0257
  -5.500  -0.4158   0.02485   0.01642  -0.0471   0.9813   0.0294
  -5.250  -0.3838   0.02316   0.01440  -0.0480   0.9762   0.0326
  -5.000  -0.3510   0.02154   0.01273  -0.0495   0.9721   0.0364
  -4.750  -0.3212   0.02049   0.01150  -0.0500   0.9659   0.0428
  -4.500  -0.2888   0.01947   0.01046  -0.0514   0.9607   0.0533
  -4.250  -0.2561   0.01862   0.00953  -0.0527   0.9559   0.0671
  -4.000  -0.2257   0.01790   0.00876  -0.0536   0.9493   0.0834
  -3.750  -0.1910   0.01708   0.00800  -0.0553   0.9449   0.1048
  -3.500  -0.1619   0.01632   0.00743  -0.0560   0.9378   0.1478
  -3.250  -0.1305   0.01537   0.00690  -0.0574   0.9322   0.2537
  -3.000  -0.1057   0.01428   0.00674  -0.0573   0.9253   0.4683
  -2.750  -0.0773   0.01404   0.00681  -0.0570   0.9191   0.5849
  -2.500  -0.0481   0.01400   0.00680  -0.0568   0.9130   0.6454
  -2.250  -0.0209   0.01402   0.00683  -0.0561   0.9061   0.6917
  -2.000   0.0083   0.01403   0.00681  -0.0557   0.9008   0.7300
  -1.750   0.0331   0.01404   0.00679  -0.0546   0.8931   0.7559
  -1.500   0.0630   0.01401   0.00671  -0.0545   0.8882   0.7804
  -1.250   0.0864   0.01401   0.00668  -0.0532   0.8798   0.8037
  -1.000   0.1163   0.01393   0.00654  -0.0531   0.8746   0.8213
  -0.750   0.1422   0.01391   0.00647  -0.0526   0.8667   0.8349
  -0.500   0.1730   0.01383   0.00633  -0.0530   0.8610   0.8477
  -0.250   0.1996   0.01379   0.00626  -0.0526   0.8525   0.8615
   0.000   0.2312   0.01368   0.00611  -0.0529   0.8461   0.8754
   0.250   0.2591   0.01362   0.00606  -0.0527   0.8360   0.8912
   0.500   0.2915   0.01354   0.00597  -0.0534   0.8271   0.9077
   0.750   0.3283   0.01341   0.00582  -0.0548   0.8182   0.9252
   1.000   0.3653   0.01330   0.00571  -0.0565   0.8058   0.9466
   1.250   0.4039   0.01316   0.00555  -0.0584   0.7919   0.9722
   1.500   0.4387   0.01306   0.00541  -0.0598   0.7775   1.0000
   1.750   0.4626   0.01307   0.00537  -0.0591   0.7638   1.0000
   2.000   0.4876   0.01311   0.00538  -0.0585   0.7508   1.0000
   2.250   0.5131   0.01318   0.00545  -0.0581   0.7380   1.0000
   2.500   0.5390   0.01324   0.00550  -0.0576   0.7244   1.0000
   2.750   0.5649   0.01330   0.00556  -0.0571   0.7099   1.0000
   3.000   0.5910   0.01337   0.00563  -0.0566   0.6945   1.0000
   3.250   0.6171   0.01344   0.00572  -0.0561   0.6779   1.0000
   3.500   0.6425   0.01356   0.00585  -0.0555   0.6585   1.0000
   3.750   0.6680   0.01366   0.00596  -0.0548   0.6373   1.0000
   4.000   0.6929   0.01381   0.00610  -0.0541   0.6126   1.0000
   4.250   0.7176   0.01397   0.00628  -0.0532   0.5835   1.0000
   4.500   0.7417   0.01420   0.00644  -0.0523   0.5491   1.0000
   4.750   0.7648   0.01451   0.00663  -0.0512   0.5086   1.0000
   5.000   0.7867   0.01492   0.00689  -0.0500   0.4579   1.0000
   5.250   0.8070   0.01552   0.00724  -0.0486   0.4078   1.0000
   5.500   0.8273   0.01617   0.00770  -0.0475   0.3619   1.0000
   5.750   0.8476   0.01686   0.00820  -0.0463   0.3216   1.0000
   6.000   0.8677   0.01756   0.00875  -0.0453   0.2876   1.0000
   6.250   0.8882   0.01825   0.00935  -0.0443   0.2588   1.0000
   6.500   0.9093   0.01891   0.00998  -0.0434   0.2323   1.0000
   6.750   0.9305   0.01955   0.01068  -0.0426   0.2061   1.0000
   7.000   0.9504   0.02029   0.01135  -0.0416   0.1736   1.0000
   7.250   0.9692   0.02117   0.01210  -0.0405   0.1371   1.0000
   7.500   0.9868   0.02221   0.01302  -0.0393   0.1114   1.0000
   7.750   1.0037   0.02333   0.01409  -0.0379   0.0951   1.0000
   8.000   1.0206   0.02444   0.01521  -0.0366   0.0832   1.0000
   8.250   1.0372   0.02555   0.01638  -0.0352   0.0744   1.0000
   8.500   1.0516   0.02683   0.01769  -0.0337   0.0676   1.0000
   8.750   1.0689   0.02784   0.01891  -0.0324   0.0608   1.0000
   9.000   1.0819   0.02914   0.02021  -0.0308   0.0549   1.0000
   9.250   1.0984   0.03013   0.02142  -0.0295   0.0484   1.0000
   9.500   1.1108   0.03133   0.02270  -0.0280   0.0417   1.0000
   9.750   1.1228   0.03250   0.02406  -0.0263   0.0363   1.0000
  10.000   1.1298   0.03400   0.02564  -0.0242   0.0314   1.0000
  10.250   1.1380   0.03557   0.02743  -0.0221   0.0264   1.0000
  10.500   1.1401   0.03747   0.02935  -0.0201   0.0228   1.0000
  10.750   1.1464   0.03935   0.03151  -0.0182   0.0195   1.0000
  11.000   1.1502   0.04127   0.03364  -0.0167   0.0173   1.0000
  11.250   1.1508   0.04352   0.03602  -0.0152   0.0161   1.0000
  11.500   1.1472   0.04641   0.03904  -0.0139   0.0152   1.0000
  11.750   1.1462   0.04937   0.04227  -0.0127   0.0146   1.0000
  12.000   1.1430   0.05269   0.04587  -0.0119   0.0140   1.0000
  12.250   1.1382   0.05625   0.04968  -0.0115   0.0137   1.0000
  12.500   1.1305   0.06030   0.05399  -0.0116   0.0133   1.0000
  12.750   1.1211   0.06473   0.05867  -0.0123   0.0132   1.0000
  13.000   1.1085   0.06986   0.06406  -0.0138   0.0130   1.0000
  13.250   1.0937   0.07567   0.07010  -0.0161   0.0129   1.0000
  13.500   1.0780   0.08202   0.07668  -0.0192   0.0129   1.0000
  13.750   1.0595   0.08946   0.08434  -0.0234   0.0130   1.0000
  14.000   1.0392   0.09798   0.09306  -0.0286   0.0132   1.0000
  14.250   1.0173   0.10771   0.10296  -0.0348   0.0134   1.0000
  14.500   0.9948   0.11835   0.11373  -0.0414   0.0138   1.0000
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