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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 50,000
Max Cl/Cd: 35.14 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1510-il-50000-n5.txt
Download as CSV file: xf-hq1510-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5129   0.09503   0.08806  -0.0271   1.0000   0.0424
  -9.500  -0.5161   0.08987   0.08297  -0.0299   1.0000   0.0420
  -9.250  -0.5211   0.08423   0.07740  -0.0334   1.0000   0.0416
  -9.000  -0.5294   0.07816   0.07139  -0.0378   1.0000   0.0411
  -8.750  -0.5437   0.07273   0.06601  -0.0414   1.0000   0.0406
  -8.500  -0.5586   0.06801   0.06126  -0.0434   1.0000   0.0402
  -8.250  -0.5687   0.06352   0.05666  -0.0446   1.0000   0.0398
  -8.000  -0.5756   0.05919   0.05215  -0.0451   1.0000   0.0401
  -7.750  -0.5786   0.05511   0.04782  -0.0450   1.0000   0.0407
  -7.500  -0.5784   0.05117   0.04354  -0.0444   1.0000   0.0419
  -7.250  -0.5751   0.04736   0.03927  -0.0434   1.0000   0.0434
  -7.000  -0.5681   0.04382   0.03516  -0.0421   1.0000   0.0448
  -6.750  -0.5576   0.04051   0.03149  -0.0407   1.0000   0.0462
  -6.500  -0.5440   0.03784   0.02860  -0.0394   1.0000   0.0479
  -6.250  -0.5284   0.03544   0.02592  -0.0379   1.0000   0.0503
  -6.000  -0.5116   0.03338   0.02347  -0.0364   1.0000   0.0555
  -5.750  -0.4942   0.03136   0.02112  -0.0349   1.0000   0.0607
  -5.500  -0.4756   0.02962   0.01922  -0.0334   1.0000   0.0664
  -5.250  -0.4574   0.02814   0.01759  -0.0318   1.0000   0.0760
  -5.000  -0.4381   0.02679   0.01601  -0.0301   1.0000   0.0857
  -4.750  -0.4204   0.02569   0.01486  -0.0285   1.0000   0.0991
  -4.500  -0.4027   0.02455   0.01368  -0.0268   1.0000   0.1108
  -4.250  -0.3853   0.02354   0.01268  -0.0253   1.0000   0.1275
  -4.000  -0.3674   0.02254   0.01175  -0.0240   1.0000   0.1509
  -3.750  -0.3490   0.02145   0.01080  -0.0231   1.0000   0.1866
  -3.500  -0.3319   0.02008   0.01000  -0.0223   1.0000   0.2791
  -3.250  -0.3192   0.01891   0.00994  -0.0198   1.0000   0.4772
  -3.000  -0.3063   0.01879   0.01015  -0.0163   1.0000   0.6018
  -2.750  -0.2929   0.01886   0.01025  -0.0130   1.0000   0.6749
  -2.500  -0.2754   0.01901   0.01041  -0.0102   0.9965   0.7365
  -2.250  -0.2516   0.01919   0.01055  -0.0081   0.9880   0.7972
  -2.000  -0.2247   0.01929   0.01055  -0.0069   0.9802   0.8457
  -1.750  -0.1886   0.01937   0.01049  -0.0076   0.9736   0.8870
  -1.500  -0.1372   0.01951   0.01040  -0.0118   0.9694   0.9238
  -1.250  -0.0832   0.01958   0.01023  -0.0173   0.9640   0.9483
  -1.000  -0.0272   0.01966   0.01009  -0.0237   0.9589   0.9676
  -0.750   0.0255   0.01968   0.00991  -0.0295   0.9523   0.9873
  -0.500   0.0687   0.01975   0.00983  -0.0338   0.9445   1.0000
  -0.250   0.0967   0.01980   0.00976  -0.0352   0.9330   1.0000
   0.000   0.1264   0.01989   0.00973  -0.0366   0.9221   1.0000
   0.250   0.1610   0.02001   0.00976  -0.0388   0.9127   1.0000
   0.500   0.1965   0.02014   0.00982  -0.0410   0.9033   1.0000
   0.750   0.2264   0.02030   0.00992  -0.0420   0.8922   1.0000
   1.000   0.2576   0.02047   0.01005  -0.0431   0.8816   1.0000
   1.250   0.2923   0.02061   0.01017  -0.0447   0.8720   1.0000
   1.500   0.3243   0.02077   0.01034  -0.0457   0.8611   1.0000
   1.750   0.3537   0.02093   0.01051  -0.0461   0.8486   1.0000
   2.000   0.3864   0.02094   0.01055  -0.0467   0.8342   1.0000
   2.250   0.4204   0.02083   0.01047  -0.0471   0.8182   1.0000
   2.500   0.4472   0.02081   0.01052  -0.0463   0.7994   1.0000
   2.750   0.4750   0.02080   0.01057  -0.0458   0.7823   1.0000
   3.000   0.5027   0.02083   0.01067  -0.0452   0.7665   1.0000
   3.250   0.5304   0.02083   0.01080  -0.0446   0.7501   1.0000
   3.500   0.5585   0.02079   0.01086  -0.0439   0.7334   1.0000
   3.750   0.5819   0.02090   0.01108  -0.0427   0.7128   1.0000
   4.000   0.6087   0.02085   0.01114  -0.0417   0.6926   1.0000
   4.250   0.6329   0.02089   0.01130  -0.0404   0.6686   1.0000
   4.500   0.6576   0.02090   0.01147  -0.0391   0.6424   1.0000
   4.750   0.6819   0.02093   0.01159  -0.0376   0.6118   1.0000
   5.000   0.7058   0.02097   0.01169  -0.0361   0.5763   1.0000
   5.250   0.7286   0.02110   0.01181  -0.0343   0.5341   1.0000
   5.500   0.7500   0.02139   0.01204  -0.0325   0.4853   1.0000
   5.750   0.7695   0.02190   0.01235  -0.0306   0.4333   1.0000
   6.000   0.7874   0.02265   0.01285  -0.0287   0.3822   1.0000
   6.250   0.8042   0.02354   0.01356  -0.0270   0.3339   1.0000
   6.500   0.8203   0.02455   0.01439  -0.0255   0.2907   1.0000
   6.750   0.8360   0.02569   0.01538  -0.0239   0.2504   1.0000
   7.000   0.8513   0.02691   0.01656  -0.0225   0.2119   1.0000
   7.250   0.8665   0.02819   0.01776  -0.0211   0.1753   1.0000
   7.500   0.8828   0.02962   0.01912  -0.0197   0.1496   1.0000
   7.750   0.8991   0.03111   0.02052  -0.0185   0.1301   1.0000
   8.000   0.9166   0.03260   0.02204  -0.0174   0.1136   1.0000
   8.250   0.9359   0.03424   0.02370  -0.0164   0.1034   1.0000
   8.500   0.9573   0.03596   0.02557  -0.0155   0.0948   1.0000
   8.750   0.9771   0.03778   0.02760  -0.0146   0.0859   1.0000
   9.000   0.9956   0.03972   0.02959  -0.0138   0.0788   1.0000
   9.250   1.0171   0.04225   0.03260  -0.0130   0.0735   1.0000
   9.500   1.0337   0.04455   0.03500  -0.0121   0.0679   1.0000
   9.750   1.0427   0.04730   0.03820  -0.0105   0.0618   1.0000
  10.000   1.0521   0.05034   0.04157  -0.0090   0.0576   1.0000
  10.250   1.0588   0.05337   0.04468  -0.0078   0.0535   1.0000
  10.500   1.0502   0.05663   0.04851  -0.0054   0.0501   1.0000
  10.750   1.0423   0.05932   0.05145  -0.0033   0.0468   1.0000
  11.000   1.0396   0.06160   0.05374  -0.0020   0.0436   1.0000
  11.250   1.0300   0.06522   0.05748  -0.0011   0.0419   1.0000
  11.500   1.0119   0.06966   0.06225  -0.0009   0.0414   1.0000
  11.750   0.9928   0.07467   0.06753  -0.0019   0.0412   1.0000
  12.000   0.9732   0.08036   0.07343  -0.0040   0.0413   1.0000
  12.250   0.9535   0.08670   0.07994  -0.0072   0.0415   1.0000
  12.500   0.9356   0.09352   0.08687  -0.0110   0.0420   1.0000
  12.750   0.9157   0.10145   0.09488  -0.0159   0.0423   1.0000
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