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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 200,000
Max Cl/Cd: 61.74 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159-il-200000-n5.txt
Download as CSV file: xf-hq159-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 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  -0.5302   0.08484   0.08137  -0.0232   1.0000   0.0094
  -9.250  -0.5334   0.07906   0.07564  -0.0264   1.0000   0.0091
  -8.750  -0.5477   0.06556   0.06220  -0.0367   1.0000   0.0088
  -8.500  -0.5625   0.05968   0.05628  -0.0411   1.0000   0.0087
  -8.250  -0.5741   0.05374   0.05020  -0.0435   1.0000   0.0087
  -8.000  -0.5824   0.04793   0.04416  -0.0445   1.0000   0.0087
  -7.750  -0.5850   0.04301   0.03897  -0.0444   1.0000   0.0086
  -7.500  -0.5853   0.03788   0.03342  -0.0435   1.0000   0.0086
  -7.250  -0.5808   0.03352   0.02859  -0.0420   1.0000   0.0087
  -7.000  -0.5712   0.03014   0.02472  -0.0403   1.0000   0.0089
  -6.750  -0.5619   0.02656   0.02066  -0.0385   1.0000   0.0092
  -6.500  -0.5476   0.02508   0.01903  -0.0371   1.0000   0.0102
  -6.250  -0.5261   0.02400   0.01776  -0.0367   0.9984   0.0114
  -6.000  -0.4942   0.02190   0.01529  -0.0381   0.9935   0.0125
  -5.750  -0.4630   0.01977   0.01279  -0.0390   0.9884   0.0132
  -5.500  -0.4300   0.01810   0.01086  -0.0403   0.9843   0.0142
  -5.250  -0.3996   0.01664   0.00921  -0.0410   0.9783   0.0153
  -5.000  -0.3664   0.01572   0.00821  -0.0426   0.9737   0.0186
  -4.750  -0.3347   0.01490   0.00727  -0.0436   0.9677   0.0217
  -4.500  -0.3030   0.01393   0.00619  -0.0446   0.9616   0.0264
  -4.250  -0.2707   0.01331   0.00551  -0.0457   0.9555   0.0364
  -4.000  -0.2396   0.01280   0.00504  -0.0466   0.9484   0.0535
  -3.750  -0.2079   0.01233   0.00461  -0.0477   0.9419   0.0766
  -3.500  -0.1778   0.01183   0.00416  -0.0484   0.9343   0.1061
  -3.250  -0.1484   0.01123   0.00380  -0.0490   0.9268   0.1711
  -3.000  -0.1202   0.01047   0.00346  -0.0496   0.9193   0.2871
  -2.500  -0.0671   0.00936   0.00317  -0.0494   0.9038   0.5384
  -2.250  -0.0412   0.00919   0.00315  -0.0488   0.8947   0.6023
  -2.000  -0.0140   0.00909   0.00311  -0.0484   0.8868   0.6465
  -1.750   0.0122   0.00903   0.00309  -0.0477   0.8783   0.6858
  -1.500   0.0382   0.00898   0.00306  -0.0469   0.8692   0.7159
  -1.250   0.0651   0.00896   0.00300  -0.0464   0.8607   0.7370
  -1.000   0.0910   0.00892   0.00296  -0.0457   0.8511   0.7563
  -0.750   0.1169   0.00890   0.00293  -0.0450   0.8414   0.7751
  -0.500   0.1434   0.00887   0.00288  -0.0445   0.8328   0.7903
  -0.250   0.1699   0.00884   0.00283  -0.0440   0.8231   0.8018
   0.000   0.1962   0.00881   0.00278  -0.0434   0.8116   0.8136
   0.250   0.2222   0.00878   0.00273  -0.0428   0.7986   0.8260
   0.500   0.2482   0.00875   0.00268  -0.0421   0.7850   0.8391
   0.750   0.2743   0.00871   0.00264  -0.0414   0.7712   0.8533
   1.000   0.3008   0.00868   0.00260  -0.0409   0.7568   0.8691
   1.250   0.3282   0.00866   0.00259  -0.0405   0.7427   0.8872
   1.500   0.3578   0.00864   0.00260  -0.0406   0.7294   0.9076
   1.750   0.3916   0.00864   0.00262  -0.0417   0.7153   0.9320
   2.000   0.4285   0.00866   0.00263  -0.0436   0.6996   0.9628
   2.250   0.4643   0.00871   0.00268  -0.0453   0.6821   1.0000
   2.500   0.4898   0.00882   0.00275  -0.0448   0.6632   1.0000
   2.750   0.5153   0.00895   0.00282  -0.0443   0.6423   1.0000
   3.000   0.5407   0.00909   0.00291  -0.0438   0.6171   1.0000
   3.250   0.5656   0.00928   0.00301  -0.0432   0.5843   1.0000
   3.500   0.5896   0.00955   0.00315  -0.0423   0.5397   1.0000
   3.750   0.6125   0.00993   0.00330  -0.0414   0.4834   1.0000
   4.000   0.6344   0.01045   0.00353  -0.0404   0.4194   1.0000
   4.250   0.6561   0.01105   0.00383  -0.0395   0.3535   1.0000
   4.750   0.7014   0.01218   0.00458  -0.0381   0.2605   1.0000
   5.000   0.7255   0.01263   0.00497  -0.0377   0.2336   1.0000
   5.250   0.7493   0.01310   0.00537  -0.0372   0.2037   1.0000
   5.500   0.7726   0.01365   0.00579  -0.0366   0.1647   1.0000
   5.750   0.7949   0.01433   0.00628  -0.0360   0.1231   1.0000
   6.000   0.8169   0.01506   0.00686  -0.0353   0.0918   1.0000
   6.250   0.8391   0.01579   0.00753  -0.0346   0.0694   1.0000
   6.500   0.8614   0.01648   0.00816  -0.0340   0.0544   1.0000
   6.750   0.8844   0.01708   0.00881  -0.0333   0.0454   1.0000
   7.000   0.9072   0.01771   0.00953  -0.0326   0.0401   1.0000
   7.250   0.9293   0.01840   0.01026  -0.0319   0.0330   1.0000
   7.500   0.9518   0.01901   0.01090  -0.0313   0.0234   1.0000
   7.750   0.9729   0.01982   0.01173  -0.0305   0.0158   1.0000
   8.000   0.9922   0.02089   0.01294  -0.0294   0.0116   1.0000
   8.250   1.0115   0.02194   0.01412  -0.0282   0.0095   1.0000
   8.500   1.0286   0.02324   0.01554  -0.0269   0.0083   1.0000
   8.750   1.0441   0.02471   0.01718  -0.0253   0.0077   1.0000
   9.000   1.0596   0.02615   0.01883  -0.0238   0.0074   1.0000
   9.250   1.0737   0.02778   0.02067  -0.0221   0.0071   1.0000
   9.500   1.0866   0.02955   0.02266  -0.0204   0.0068   1.0000
   9.750   1.0980   0.03151   0.02486  -0.0186   0.0067   1.0000
  10.000   1.1074   0.03364   0.02725  -0.0166   0.0065   1.0000
  10.250   1.1139   0.03586   0.02974  -0.0145   0.0063   1.0000
  10.500   1.1166   0.03797   0.03209  -0.0120   0.0061   1.0000
  10.750   1.1189   0.03972   0.03404  -0.0098   0.0057   1.0000
  11.000   1.1164   0.04214   0.03669  -0.0076   0.0056   1.0000
  11.250   1.1152   0.04418   0.03895  -0.0062   0.0053   1.0000
  11.500   1.1130   0.04630   0.04118  -0.0052   0.0050   1.0000
  11.750   1.1032   0.04994   0.04508  -0.0046   0.0050   1.0000
  12.000   1.0924   0.05377   0.04910  -0.0048   0.0049   1.0000
  12.250   1.0789   0.05844   0.05400  -0.0060   0.0049   1.0000
  12.500   1.0601   0.06436   0.06013  -0.0086   0.0047   1.0000
  12.750   1.0472   0.07027   0.06627  -0.0117   0.0049   1.0000
  13.000   1.0299   0.07758   0.07377  -0.0163   0.0049   1.0000
  13.250   1.0110   0.08624   0.08262  -0.0222   0.0049   1.0000
  13.500   0.9209   0.11653   0.11331  -0.0402   0.0067   1.0000
  13.750   0.8898   0.13150   0.12829  -0.0477   0.0070   1.0000
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