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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.18 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor07-il-1000000.txt
Download as CSV file: xf-hor07-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR07 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4504   0.10483   0.10327   0.0017   1.0000   0.0119
  -8.500  -0.4451   0.10097   0.09942  -0.0003   1.0000   0.0120
  -8.250  -0.4450   0.09646   0.09494  -0.0015   1.0000   0.0124
  -8.000  -0.4370   0.09380   0.09229  -0.0026   1.0000   0.0125
  -7.750  -0.4297   0.09108   0.08958  -0.0039   1.0000   0.0128
  -7.500  -0.4229   0.08817   0.08670  -0.0056   1.0000   0.0130
  -7.250  -0.4092   0.08470   0.08310  -0.0094   0.9148   0.0134
  -7.000  -0.3997   0.08148   0.07966  -0.0121   0.8572   0.0138
  -6.750  -0.3850   0.07755   0.07561  -0.0166   0.8288   0.0143
  -6.500  -0.3623   0.07157   0.06952  -0.0254   0.8069   0.0156
  -6.000  -0.2629   0.02071   0.01700  -0.0834   0.7900   0.0123
  -5.750  -0.2301   0.01705   0.01271  -0.0861   0.7749   0.0125
  -5.250  -0.1699   0.01446   0.00957  -0.0879   0.7494   0.0131
  -5.000  -0.1399   0.01357   0.00848  -0.0885   0.7394   0.0133
  -4.750  -0.1099   0.01275   0.00745  -0.0890   0.7298   0.0135
  -4.500  -0.0800   0.01203   0.00657  -0.0895   0.7215   0.0137
  -4.250  -0.0501   0.01140   0.00579  -0.0899   0.7137   0.0140
  -4.000  -0.0203   0.01093   0.00520  -0.0902   0.7062   0.0144
  -3.750   0.0093   0.01055   0.00472  -0.0905   0.6987   0.0149
  -3.500   0.0391   0.01013   0.00420  -0.0908   0.6903   0.0154
  -3.250   0.0687   0.00981   0.00380  -0.0910   0.6830   0.0158
  -3.000   0.0989   0.00930   0.00317  -0.0914   0.6742   0.0175
  -2.750   0.1283   0.00910   0.00292  -0.0916   0.6661   0.0194
  -2.500   0.1578   0.00887   0.00263  -0.0918   0.6567   0.0227
  -2.250   0.1873   0.00864   0.00241  -0.0920   0.6474   0.0320
  -2.000   0.2165   0.00851   0.00225  -0.0922   0.6383   0.0416
  -1.750   0.2457   0.00836   0.00211  -0.0924   0.6290   0.0546
  -1.500   0.2750   0.00815   0.00201  -0.0927   0.6203   0.0928
  -1.250   0.3041   0.00809   0.00195  -0.0929   0.6113   0.1156
  -1.000   0.3331   0.00802   0.00193  -0.0931   0.6027   0.1356
  -0.750   0.3621   0.00800   0.00189  -0.0932   0.5942   0.1498
  -0.500   0.3911   0.00797   0.00186  -0.0934   0.5847   0.1619
  -0.250   0.4201   0.00795   0.00184  -0.0935   0.5756   0.1772
   0.000   0.4490   0.00794   0.00184  -0.0937   0.5659   0.1958
   0.250   0.4780   0.00792   0.00184  -0.0938   0.5554   0.2159
   0.500   0.5069   0.00791   0.00185  -0.0940   0.5441   0.2371
   0.750   0.5358   0.00791   0.00187  -0.0942   0.5317   0.2629
   1.000   0.5647   0.00790   0.00191  -0.0944   0.5184   0.2949
   1.250   0.5936   0.00791   0.00194  -0.0946   0.5045   0.3278
   1.500   0.6226   0.00786   0.00201  -0.0949   0.4904   0.3998
   1.750   0.6518   0.00766   0.00211  -0.0953   0.4761   0.5484
   2.000   0.6742   0.00670   0.00208  -0.0941   0.4605   1.0000
   2.250   0.7028   0.00686   0.00215  -0.0943   0.4434   1.0000
   2.500   0.7314   0.00704   0.00224  -0.0944   0.4249   1.0000
   2.750   0.7599   0.00722   0.00234  -0.0945   0.4074   1.0000
   3.000   0.7882   0.00745   0.00245  -0.0947   0.3817   1.0000
   3.250   0.8164   0.00774   0.00258  -0.0948   0.3496   1.0000
   3.500   0.8446   0.00800   0.00272  -0.0949   0.3286   1.0000
   3.750   0.8728   0.00822   0.00288  -0.0951   0.3121   1.0000
   4.000   0.9008   0.00850   0.00305  -0.0952   0.2876   1.0000
   4.250   0.9272   0.00936   0.00346  -0.0954   0.1907   1.0000
   4.500   0.9548   0.00974   0.00374  -0.0955   0.1740   1.0000
   4.750   0.9820   0.01022   0.00406  -0.0956   0.1354   1.0000
   5.000   1.0083   0.01099   0.00455  -0.0957   0.0728   1.0000
   5.250   1.0350   0.01158   0.00497  -0.0956   0.0421   1.0000
   5.500   1.0620   0.01201   0.00535  -0.0956   0.0340   1.0000
   5.750   1.0893   0.01233   0.00571  -0.0955   0.0321   1.0000
   6.000   1.1164   0.01264   0.00604  -0.0955   0.0307   1.0000
   6.250   1.1433   0.01298   0.00640  -0.0954   0.0292   1.0000
   6.500   1.1699   0.01338   0.00682  -0.0953   0.0281   1.0000
   6.750   1.1961   0.01384   0.00732  -0.0951   0.0269   1.0000
   7.000   1.2214   0.01445   0.00800  -0.0948   0.0256   1.0000
   7.250   1.2458   0.01521   0.00885  -0.0945   0.0246   1.0000
   7.500   1.2718   0.01555   0.00921  -0.0943   0.0243   1.0000
   7.750   1.2977   0.01587   0.00957  -0.0941   0.0238   1.0000
   8.000   1.3231   0.01627   0.01001  -0.0939   0.0231   1.0000
   8.250   1.3479   0.01673   0.01051  -0.0936   0.0225   1.0000
   8.500   1.3727   0.01716   0.01097  -0.0933   0.0217   1.0000
   8.750   1.3972   0.01760   0.01144  -0.0929   0.0209   1.0000
   9.000   1.4210   0.01813   0.01198  -0.0925   0.0200   1.0000
   9.250   1.4393   0.01939   0.01335  -0.0914   0.0185   1.0000
   9.500   1.4644   0.01962   0.01361  -0.0911   0.0180   1.0000
   9.750   1.4907   0.01966   0.01366  -0.0911   0.0172   1.0000
  10.000   1.5162   0.01980   0.01382  -0.0909   0.0160   1.0000
  10.250   1.5412   0.01997   0.01395  -0.0907   0.0147   1.0000
  10.500   1.5638   0.02045   0.01444  -0.0902   0.0131   1.0000
  10.750   1.5888   0.02061   0.01459  -0.0899   0.0112   1.0000
  11.000   1.6098   0.02121   0.01518  -0.0891   0.0095   1.0000
  11.250   1.6297   0.02190   0.01591  -0.0882   0.0085   1.0000
  11.500   1.6476   0.02273   0.01676  -0.0870   0.0077   1.0000
  11.750   1.6615   0.02390   0.01802  -0.0853   0.0071   1.0000
  12.000   1.6759   0.02486   0.01908  -0.0836   0.0069   1.0000
  12.250   1.6878   0.02591   0.02023  -0.0816   0.0066   1.0000
  12.500   1.6971   0.02705   0.02147  -0.0793   0.0064   1.0000
  12.750   1.7013   0.02831   0.02283  -0.0763   0.0062   1.0000
  13.000   1.7029   0.02984   0.02447  -0.0734   0.0061   1.0000
  13.250   1.7050   0.03164   0.02637  -0.0712   0.0059   1.0000
  13.500   1.7070   0.03372   0.02858  -0.0696   0.0058   1.0000
  13.750   1.7077   0.03613   0.03110  -0.0684   0.0056   1.0000
  14.000   1.7063   0.03898   0.03407  -0.0676   0.0054   1.0000
  14.250   1.7014   0.04238   0.03761  -0.0670   0.0053   1.0000
  14.500   1.6926   0.04638   0.04177  -0.0666   0.0051   1.0000
  14.750   1.6815   0.05076   0.04632  -0.0664   0.0050   1.0000
  15.000   1.6733   0.05490   0.05061  -0.0664   0.0050   1.0000
  15.250   1.6675   0.05880   0.05464  -0.0667   0.0049   1.0000
  15.500   1.6597   0.06304   0.05901  -0.0671   0.0049   1.0000
  15.750   1.6509   0.06752   0.06363  -0.0677   0.0049   1.0000
  16.000   1.6405   0.07235   0.06860  -0.0686   0.0048   1.0000
  16.250   1.6293   0.07753   0.07392  -0.0698   0.0048   1.0000
  16.500   1.6172   0.08307   0.07960  -0.0714   0.0048   1.0000
  16.750   1.6042   0.08895   0.08562  -0.0732   0.0048   1.0000
  17.000   1.5896   0.09522   0.09204  -0.0754   0.0047   1.0000
  17.250   1.5747   0.10174   0.09870  -0.0778   0.0047   1.0000
  17.500   1.5584   0.10868   0.10578  -0.0806   0.0047   1.0000
  17.750   1.5415   0.11585   0.11309  -0.0836   0.0047   1.0000
  18.000   1.5231   0.12355   0.12094  -0.0871   0.0047   1.0000
  18.250   1.5048   0.13149   0.12902  -0.0910   0.0047   1.0000
  18.500   1.4865   0.13962   0.13728  -0.0952   0.0047   1.0000
  18.750   1.4660   0.14859   0.14640  -0.1001   0.0047   1.0000
  19.000   1.4447   0.15827   0.15622  -0.1058   0.0047   1.0000
  19.250   1.4228   0.16864   0.16674  -0.1121   0.0048   1.0000
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