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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 100,000
Max Cl/Cd: 48.38 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1512-il-100000-n5.txt
Download as CSV file: xf-hq1512-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/12 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5690   0.08512   0.08004  -0.0379   1.0000   0.0277
 -11.000  -0.6059   0.07205   0.06692  -0.0476   1.0000   0.0268
 -10.750  -0.6393   0.06347   0.05821  -0.0540   1.0000   0.0264
 -10.500  -0.6672   0.05762   0.05218  -0.0571   1.0000   0.0259
 -10.250  -0.6898   0.05355   0.04793  -0.0574   1.0000   0.0259
 -10.000  -0.7088   0.05029   0.04446  -0.0556   1.0000   0.0260
  -9.750  -0.7198   0.04698   0.04089  -0.0538   1.0000   0.0261
  -9.500  -0.7251   0.04387   0.03747  -0.0519   1.0000   0.0265
  -9.250  -0.7260   0.04098   0.03426  -0.0498   1.0000   0.0270
  -9.000  -0.7233   0.03829   0.03123  -0.0475   1.0000   0.0276
  -8.750  -0.7174   0.03594   0.02854  -0.0453   1.0000   0.0285
  -8.500  -0.7090   0.03402   0.02623  -0.0430   1.0000   0.0299
  -8.250  -0.6996   0.03216   0.02423  -0.0409   1.0000   0.0313
  -8.000  -0.6889   0.03082   0.02283  -0.0389   1.0000   0.0326
  -7.750  -0.6778   0.02949   0.02133  -0.0366   1.0000   0.0338
  -7.500  -0.6665   0.02820   0.01989  -0.0343   1.0000   0.0351
  -7.250  -0.6537   0.02698   0.01850  -0.0321   0.9997   0.0368
  -7.000  -0.6212   0.02550   0.01680  -0.0337   0.9936   0.0404
  -6.750  -0.5905   0.02426   0.01555  -0.0353   0.9869   0.0443
  -6.500  -0.5585   0.02307   0.01418  -0.0366   0.9807   0.0486
  -6.250  -0.5280   0.02195   0.01304  -0.0379   0.9738   0.0550
  -6.000  -0.4961   0.02102   0.01203  -0.0393   0.9676   0.0640
  -5.750  -0.4654   0.02017   0.01115  -0.0405   0.9605   0.0761
  -5.500  -0.4318   0.01929   0.01036  -0.0423   0.9553   0.0953
  -5.250  -0.4033   0.01855   0.00967  -0.0430   0.9474   0.1197
  -5.000  -0.3704   0.01778   0.00905  -0.0446   0.9421   0.1563
  -4.750  -0.3437   0.01713   0.00856  -0.0450   0.9337   0.2008
  -4.500  -0.3126   0.01640   0.00806  -0.0462   0.9280   0.2615
  -4.250  -0.2881   0.01568   0.00767  -0.0461   0.9196   0.3356
  -4.000  -0.2598   0.01506   0.00751  -0.0464   0.9138   0.4423
  -3.750  -0.2346   0.01487   0.00754  -0.0456   0.9059   0.5183
  -3.500  -0.2044   0.01481   0.00751  -0.0457   0.8999   0.5704
  -3.250  -0.1774   0.01484   0.00750  -0.0452   0.8924   0.6044
  -3.000  -0.1480   0.01486   0.00745  -0.0452   0.8860   0.6326
  -2.750  -0.1211   0.01491   0.00746  -0.0446   0.8787   0.6558
  -2.500  -0.0930   0.01494   0.00741  -0.0443   0.8719   0.6770
  -2.250  -0.0658   0.01498   0.00740  -0.0438   0.8650   0.6939
  -2.000  -0.0386   0.01501   0.00736  -0.0433   0.8579   0.7092
  -1.750  -0.0112   0.01502   0.00731  -0.0429   0.8513   0.7238
  -1.500   0.0144   0.01506   0.00732  -0.0421   0.8437   0.7393
  -1.250   0.0409   0.01508   0.00732  -0.0413   0.8371   0.7551
  -1.000   0.0660   0.01510   0.00731  -0.0405   0.8292   0.7686
  -0.750   0.0934   0.01507   0.00722  -0.0402   0.8227   0.7800
  -0.500   0.1192   0.01506   0.00720  -0.0395   0.8145   0.7883
  -0.250   0.1470   0.01501   0.00710  -0.0394   0.8079   0.7976
   0.000   0.1729   0.01500   0.00708  -0.0389   0.7996   0.8068
   0.250   0.2005   0.01496   0.00703  -0.0386   0.7928   0.8157
   0.500   0.2263   0.01494   0.00700  -0.0380   0.7841   0.8259
   0.750   0.2526   0.01489   0.00695  -0.0374   0.7748   0.8354
   1.000   0.2806   0.01476   0.00680  -0.0370   0.7656   0.8450
   1.250   0.3057   0.01468   0.00674  -0.0361   0.7532   0.8559
   1.500   0.3317   0.01459   0.00665  -0.0354   0.7406   0.8668
   1.750   0.3587   0.01449   0.00657  -0.0348   0.7280   0.8779
   2.000   0.3869   0.01442   0.00653  -0.0346   0.7163   0.8897
   2.250   0.4171   0.01435   0.00648  -0.0347   0.7062   0.9022
   2.500   0.4482   0.01433   0.00653  -0.0352   0.6939   0.9154
   2.750   0.4820   0.01432   0.00659  -0.0363   0.6812   0.9294
   3.000   0.5175   0.01431   0.00662  -0.0378   0.6672   0.9448
   3.250   0.5545   0.01431   0.00666  -0.0396   0.6520   0.9616
   3.500   0.5919   0.01430   0.00671  -0.0416   0.6351   0.9810
   3.750   0.6250   0.01434   0.00677  -0.0428   0.6166   1.0000
   4.000   0.6448   0.01445   0.00686  -0.0415   0.5969   1.0000
   4.250   0.6667   0.01456   0.00693  -0.0403   0.5751   1.0000
   4.500   0.6888   0.01471   0.00707  -0.0393   0.5492   1.0000
   4.750   0.7110   0.01491   0.00719  -0.0381   0.5185   1.0000
   5.000   0.7327   0.01518   0.00734  -0.0369   0.4829   1.0000
   5.250   0.7533   0.01557   0.00756  -0.0356   0.4434   1.0000
   5.500   0.7731   0.01606   0.00786  -0.0343   0.4024   1.0000
   5.750   0.7923   0.01663   0.00824  -0.0329   0.3635   1.0000
   6.000   0.8113   0.01725   0.00867  -0.0316   0.3286   1.0000
   6.250   0.8304   0.01790   0.00916  -0.0304   0.2992   1.0000
   6.500   0.8498   0.01853   0.00971  -0.0293   0.2746   1.0000
   6.750   0.8691   0.01919   0.01028  -0.0282   0.2529   1.0000
   7.000   0.8891   0.01978   0.01088  -0.0272   0.2312   1.0000
   7.250   0.9081   0.02043   0.01148  -0.0260   0.2089   1.0000
   7.500   0.9274   0.02106   0.01214  -0.0250   0.1843   1.0000
   7.750   0.9455   0.02178   0.01282  -0.0237   0.1599   1.0000
   8.000   0.9616   0.02265   0.01359  -0.0223   0.1361   1.0000
   8.250   0.9767   0.02362   0.01447  -0.0208   0.1164   1.0000
   8.500   0.9909   0.02466   0.01544  -0.0192   0.1021   1.0000
   8.750   1.0047   0.02572   0.01649  -0.0176   0.0923   1.0000
   9.000   1.0167   0.02686   0.01764  -0.0157   0.0856   1.0000
   9.250   1.0291   0.02791   0.01877  -0.0138   0.0801   1.0000
   9.500   1.0402   0.02900   0.01992  -0.0119   0.0751   1.0000
   9.750   1.0492   0.03030   0.02120  -0.0099   0.0712   1.0000
  10.000   1.0621   0.03143   0.02250  -0.0084   0.0676   1.0000
  10.250   1.0739   0.03271   0.02388  -0.0068   0.0647   1.0000
  10.500   1.0846   0.03406   0.02529  -0.0053   0.0621   1.0000
  10.750   1.0949   0.03569   0.02690  -0.0039   0.0597   1.0000
  11.000   1.1078   0.03708   0.02854  -0.0027   0.0575   1.0000
  11.250   1.1191   0.03859   0.03024  -0.0014   0.0549   1.0000
  11.500   1.1299   0.04020   0.03200  -0.0003   0.0529   1.0000
  11.750   1.1398   0.04191   0.03382   0.0008   0.0511   1.0000
  12.000   1.1482   0.04370   0.03567   0.0018   0.0492   1.0000
  12.250   1.1555   0.04584   0.03793   0.0028   0.0472   1.0000
  12.500   1.1569   0.04798   0.04039   0.0039   0.0453   1.0000
  12.750   1.1568   0.05024   0.04289   0.0047   0.0430   1.0000
  13.000   1.1562   0.05251   0.04530   0.0052   0.0410   1.0000
  13.250   1.1547   0.05475   0.04758   0.0053   0.0389   1.0000
  13.500   1.1541   0.05764   0.05056   0.0055   0.0374   1.0000
  13.750   1.1457   0.06124   0.05451   0.0051   0.0360   1.0000
  14.000   1.1365   0.06517   0.05873   0.0041   0.0344   1.0000
  14.250   1.1275   0.06929   0.06306   0.0028   0.0329   1.0000
  14.500   1.1185   0.07356   0.06749   0.0011   0.0316   1.0000
  14.750   1.1095   0.07807   0.07213  -0.0010   0.0305   1.0000
  15.000   1.1006   0.08285   0.07699  -0.0034   0.0296   1.0000
  15.250   1.0911   0.08798   0.08220  -0.0059   0.0287   1.0000
  15.500   1.0735   0.09519   0.08964  -0.0099   0.0285   1.0000
  15.750   1.0521   0.10369   0.09838  -0.0149   0.0282   1.0000
  16.000   1.0299   0.11286   0.10775  -0.0204   0.0282   1.0000
  16.250   1.0060   0.12297   0.11802  -0.0266   0.0284   1.0000
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