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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 500,000
Max Cl/Cd: 98 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor07-il-500000.txt
Download as CSV file: xf-hor07-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4271   0.10118   0.09901  -0.0007   1.0000   0.0199
  -8.000  -0.4242   0.09747   0.09533  -0.0053   1.0000   0.0207
  -7.750  -0.4192   0.09394   0.09183  -0.0083   1.0000   0.0208
  -7.500  -0.4090   0.09006   0.08797  -0.0122   1.0000   0.0209
  -7.250  -0.3959   0.08583   0.08375  -0.0170   1.0000   0.0210
  -7.000  -0.3913   0.08072   0.07866  -0.0188   1.0000   0.0216
  -6.750  -0.3772   0.07807   0.07603  -0.0202   1.0000   0.0221
  -6.500  -0.3609   0.07493   0.07289  -0.0233   1.0000   0.0226
  -6.250  -0.3423   0.07128   0.06926  -0.0276   1.0000   0.0232
  -6.000  -0.3108   0.06648   0.06441  -0.0359   0.9638   0.0243
  -5.750  -0.2810   0.06132   0.05912  -0.0438   0.9153   0.0258
  -5.500  -0.2392   0.05454   0.05209  -0.0555   0.8776   0.0274
  -5.250  -0.2057   0.04389   0.04116  -0.0673   0.8561   0.0283
  -5.000  -0.1827   0.04191   0.03903  -0.0687   0.8353   0.0291
  -4.750  -0.1161   0.02170   0.01715  -0.0865   0.8267   0.0211
  -4.500  -0.0834   0.01780   0.01267  -0.0887   0.8107   0.0203
  -4.250  -0.0532   0.01674   0.01125  -0.0892   0.7950   0.0208
  -4.000  -0.0224   0.01521   0.00933  -0.0900   0.7819   0.0211
  -3.750   0.0081   0.01383   0.00765  -0.0905   0.7705   0.0212
  -3.500   0.0388   0.01243   0.00600  -0.0911   0.7603   0.0219
  -3.250   0.0686   0.01178   0.00526  -0.0915   0.7504   0.0231
  -3.000   0.0981   0.01137   0.00474  -0.0917   0.7412   0.0249
  -2.750   0.1276   0.01105   0.00431  -0.0918   0.7321   0.0271
  -2.500   0.1577   0.01050   0.00370  -0.0922   0.7234   0.0323
  -2.250   0.1872   0.01018   0.00331  -0.0924   0.7153   0.0432
  -2.000   0.2169   0.00987   0.00299  -0.0927   0.7068   0.0577
  -1.750   0.2462   0.00959   0.00281  -0.0930   0.6993   0.0957
  -1.500   0.2753   0.00945   0.00278  -0.0932   0.6912   0.1338
  -1.250   0.3041   0.00942   0.00272  -0.0933   0.6836   0.1535
  -1.000   0.3331   0.00935   0.00266  -0.0934   0.6753   0.1680
  -0.750   0.3620   0.00931   0.00261  -0.0935   0.6676   0.1835
  -0.500   0.3910   0.00926   0.00256  -0.0936   0.6590   0.1999
  -0.250   0.4199   0.00922   0.00252  -0.0938   0.6505   0.2184
   0.000   0.4487   0.00916   0.00250  -0.0939   0.6416   0.2406
   0.250   0.4777   0.00908   0.00248  -0.0941   0.6322   0.2680
   0.500   0.5066   0.00903   0.00248  -0.0942   0.6228   0.3007
   0.750   0.5356   0.00893   0.00247  -0.0944   0.6129   0.3419
   1.000   0.5647   0.00870   0.00254  -0.0948   0.6030   0.4490
   1.250   0.5861   0.00743   0.00242  -0.0933   0.5940   1.0000
   1.500   0.6149   0.00752   0.00243  -0.0934   0.5833   1.0000
   1.750   0.6436   0.00762   0.00247  -0.0935   0.5723   1.0000
   2.000   0.6723   0.00773   0.00252  -0.0935   0.5615   1.0000
   2.250   0.7009   0.00785   0.00257  -0.0936   0.5504   1.0000
   2.500   0.7295   0.00797   0.00264  -0.0937   0.5376   1.0000
   2.750   0.7579   0.00810   0.00271  -0.0937   0.5216   1.0000
   3.000   0.7863   0.00825   0.00280  -0.0938   0.5028   1.0000
   3.250   0.8144   0.00845   0.00290  -0.0938   0.4800   1.0000
   3.500   0.8423   0.00870   0.00302  -0.0939   0.4548   1.0000
   3.750   0.8703   0.00895   0.00319  -0.0940   0.4341   1.0000
   4.000   0.8983   0.00917   0.00335  -0.0940   0.4150   1.0000
   4.250   0.9261   0.00945   0.00353  -0.0941   0.3899   1.0000
   4.500   0.9538   0.00974   0.00372  -0.0941   0.3627   1.0000
   4.750   0.9810   0.01014   0.00398  -0.0942   0.3282   1.0000
   5.000   1.0078   0.01065   0.00430  -0.0943   0.2832   1.0000
   5.250   1.0311   0.01218   0.00513  -0.0943   0.1422   1.0000
   5.500   1.0546   0.01360   0.00606  -0.0942   0.0572   1.0000
   5.750   1.0807   0.01421   0.00665  -0.0940   0.0464   1.0000
   6.000   1.1065   0.01484   0.00732  -0.0937   0.0421   1.0000
   6.250   1.1326   0.01533   0.00787  -0.0935   0.0402   1.0000
   6.500   1.1582   0.01587   0.00846  -0.0932   0.0384   1.0000
   6.750   1.1833   0.01647   0.00911  -0.0929   0.0367   1.0000
   7.000   1.2075   0.01721   0.00990  -0.0925   0.0354   1.0000
   7.250   1.2300   0.01817   0.01094  -0.0918   0.0343   1.0000
   7.500   1.2498   0.01951   0.01239  -0.0908   0.0333   1.0000
   7.750   1.2715   0.02047   0.01343  -0.0900   0.0326   1.0000
   8.000   1.2953   0.02098   0.01401  -0.0895   0.0318   1.0000
   8.250   1.3187   0.02152   0.01461  -0.0890   0.0305   1.0000
   8.500   1.3414   0.02213   0.01527  -0.0884   0.0291   1.0000
   8.750   1.3635   0.02275   0.01594  -0.0877   0.0277   1.0000
   9.000   1.3836   0.02361   0.01683  -0.0869   0.0263   1.0000
   9.250   1.3946   0.02603   0.01935  -0.0848   0.0247   1.0000
   9.500   1.4173   0.02628   0.01970  -0.0841   0.0239   1.0000
   9.750   1.4380   0.02682   0.02033  -0.0833   0.0226   1.0000
  10.000   1.4578   0.02735   0.02093  -0.0824   0.0210   1.0000
  10.250   1.4756   0.02802   0.02162  -0.0814   0.0196   1.0000
  10.500   1.4847   0.02986   0.02359  -0.0791   0.0178   1.0000
  10.750   1.5019   0.03033   0.02416  -0.0779   0.0163   1.0000
  11.000   1.5172   0.03086   0.02474  -0.0765   0.0151   1.0000
  11.250   1.5271   0.03171   0.02561  -0.0745   0.0142   1.0000
  11.500   1.5235   0.03406   0.02808  -0.0710   0.0134   1.0000
  11.750   1.5313   0.03545   0.02962  -0.0692   0.0128   1.0000
  12.000   1.5370   0.03722   0.03155  -0.0676   0.0122   1.0000
  12.250   1.5421   0.03915   0.03362  -0.0663   0.0117   1.0000
  12.500   1.5478   0.04110   0.03568  -0.0653   0.0112   1.0000
  12.750   1.5529   0.04318   0.03785  -0.0647   0.0109   1.0000
  13.000   1.5570   0.04549   0.04024  -0.0642   0.0106   1.0000
  13.250   1.5570   0.04837   0.04323  -0.0637   0.0103   1.0000
  13.500   1.5491   0.05230   0.04733  -0.0630   0.0100   1.0000
  13.750   1.5411   0.05640   0.05162  -0.0624   0.0098   1.0000
  14.000   1.5361   0.06018   0.05560  -0.0623   0.0097   1.0000
  14.250   1.5288   0.06438   0.06001  -0.0625   0.0096   1.0000
  14.500   1.5192   0.06900   0.06482  -0.0629   0.0095   1.0000
  14.750   1.5068   0.07415   0.07018  -0.0637   0.0094   1.0000
  15.000   1.4931   0.07968   0.07591  -0.0650   0.0093   1.0000
  15.250   1.4771   0.08583   0.08227  -0.0668   0.0092   1.0000
  15.500   1.4593   0.09266   0.08931  -0.0692   0.0092   1.0000
  15.750   1.4406   0.10006   0.09692  -0.0723   0.0092   1.0000
  16.000   1.4196   0.10821   0.10527  -0.0761   0.0092   1.0000
  16.250   1.3971   0.11715   0.11440  -0.0806   0.0092   1.0000
  16.500   1.3730   0.12694   0.12439  -0.0860   0.0092   1.0000
  16.750   1.3473   0.13769   0.13533  -0.0923   0.0093   1.0000
  17.000   1.3187   0.15006   0.14788  -0.1000   0.0095   1.0000
  17.250   1.2832   0.16597   0.16396  -0.1102   0.0097   1.0000
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