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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 200,000
Max Cl/Cd: 72.98 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor07-il-200000-n5.txt
Download as CSV file: xf-hor07-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4340   0.11023   0.10677  -0.0020   1.0000   0.0283
  -8.500  -0.4298   0.10696   0.10353  -0.0050   1.0000   0.0285
  -8.250  -0.4243   0.10351   0.10011  -0.0075   1.0000   0.0286
  -8.000  -0.4190   0.10003   0.09666  -0.0098   1.0000   0.0287
  -7.750  -0.4120   0.09644   0.09311  -0.0124   1.0000   0.0288
  -7.500  -0.4016   0.09250   0.08919  -0.0158   1.0000   0.0288
  -7.250  -0.3896   0.08839   0.08510  -0.0195   1.0000   0.0288
  -6.750  -0.3718   0.07812   0.07485  -0.0232   1.0000   0.0210
  -6.500  -0.3564   0.07405   0.07079  -0.0273   1.0000   0.0207
  -6.250  -0.3275   0.06733   0.06402  -0.0378   0.9698   0.0214
  -6.000  -0.2966   0.06155   0.05815  -0.0463   0.9345   0.0213
  -5.750  -0.2696   0.05684   0.05332  -0.0522   0.9027   0.0208
  -5.500  -0.2400   0.05142   0.04773  -0.0591   0.8767   0.0202
  -5.250  -0.2040   0.04427   0.04031  -0.0679   0.8576   0.0195
  -4.750  -0.1073   0.02150   0.01530  -0.0899   0.8288   0.0184
  -4.500  -0.0769   0.01951   0.01275  -0.0907   0.8092   0.0188
  -4.250  -0.0472   0.01807   0.01088  -0.0912   0.7917   0.0194
  -4.000  -0.0178   0.01694   0.00940  -0.0915   0.7770   0.0202
  -3.750   0.0116   0.01606   0.00823  -0.0917   0.7650   0.0211
  -3.500   0.0407   0.01532   0.00732  -0.0919   0.7541   0.0230
  -3.250   0.0696   0.01488   0.00677  -0.0921   0.7432   0.0254
  -3.000   0.0991   0.01434   0.00606  -0.0923   0.7330   0.0277
  -2.750   0.1286   0.01378   0.00536  -0.0926   0.7237   0.0314
  -2.500   0.1581   0.01341   0.00485  -0.0927   0.7142   0.0380
  -2.250   0.1874   0.01304   0.00441  -0.0930   0.7054   0.0497
  -2.000   0.2165   0.01266   0.00412  -0.0932   0.6962   0.0744
  -1.750   0.2455   0.01243   0.00396  -0.0934   0.6867   0.1096
  -1.500   0.2741   0.01233   0.00383  -0.0935   0.6770   0.1357
  -1.250   0.3028   0.01226   0.00373  -0.0936   0.6665   0.1584
  -1.000   0.3316   0.01219   0.00362  -0.0937   0.6567   0.1742
  -0.750   0.3602   0.01213   0.00353  -0.0937   0.6474   0.1907
  -0.500   0.3889   0.01206   0.00350  -0.0938   0.6374   0.2139
  -0.250   0.4176   0.01200   0.00343  -0.0939   0.6278   0.2334
   0.000   0.4462   0.01195   0.00337  -0.0940   0.6181   0.2521
   0.250   0.4749   0.01188   0.00334  -0.0941   0.6082   0.2743
   0.500   0.5035   0.01183   0.00332  -0.0942   0.5990   0.3011
   0.750   0.5320   0.01177   0.00331  -0.0943   0.5894   0.3343
   1.000   0.5605   0.01166   0.00335  -0.0944   0.5800   0.4027
   1.250   0.5866   0.01095   0.00340  -0.0941   0.5711   0.6766
   1.500   0.6095   0.01041   0.00322  -0.0925   0.5614   1.0000
   1.750   0.6380   0.01054   0.00327  -0.0925   0.5513   1.0000
   2.000   0.6664   0.01068   0.00333  -0.0926   0.5406   1.0000
   2.250   0.6948   0.01081   0.00341  -0.0926   0.5292   1.0000
   2.500   0.7232   0.01095   0.00351  -0.0926   0.5182   1.0000
   2.750   0.7514   0.01111   0.00364  -0.0926   0.5077   1.0000
   3.000   0.7796   0.01128   0.00377  -0.0926   0.4971   1.0000
   3.250   0.8078   0.01145   0.00393  -0.0927   0.4868   1.0000
   3.500   0.8358   0.01164   0.00410  -0.0927   0.4763   1.0000
   3.750   0.8634   0.01187   0.00429  -0.0926   0.4589   1.0000
   4.000   0.8904   0.01220   0.00447  -0.0925   0.4293   1.0000
   4.250   0.9171   0.01258   0.00469  -0.0924   0.3936   1.0000
   4.500   0.9437   0.01299   0.00495  -0.0923   0.3577   1.0000
   4.750   0.9697   0.01354   0.00530  -0.0922   0.3142   1.0000
   5.000   0.9954   0.01415   0.00570  -0.0921   0.2495   1.0000
   5.250   1.0180   0.01553   0.00651  -0.0920   0.1698   1.0000
   5.500   1.0425   0.01641   0.00723  -0.0918   0.1010   1.0000
   5.750   1.0660   0.01747   0.00808  -0.0916   0.0647   1.0000
   6.000   1.0907   0.01820   0.00880  -0.0912   0.0524   1.0000
   6.250   1.1153   0.01887   0.00950  -0.0909   0.0460   1.0000
   6.500   1.1391   0.01966   0.01032  -0.0905   0.0420   1.0000
   6.750   1.1632   0.02033   0.01113  -0.0900   0.0401   1.0000
   7.000   1.1864   0.02108   0.01199  -0.0895   0.0384   1.0000
   7.250   1.2088   0.02190   0.01291  -0.0888   0.0369   1.0000
   7.500   1.2303   0.02280   0.01389  -0.0881   0.0357   1.0000
   7.750   1.2508   0.02378   0.01496  -0.0872   0.0347   1.0000
   8.000   1.2698   0.02491   0.01618  -0.0862   0.0338   1.0000
   8.250   1.2869   0.02625   0.01759  -0.0849   0.0330   1.0000
   8.500   1.3021   0.02788   0.01929  -0.0833   0.0322   1.0000
   8.750   1.3205   0.02902   0.02054  -0.0821   0.0317   1.0000
   9.000   1.3395   0.02996   0.02161  -0.0810   0.0306   1.0000
   9.250   1.3579   0.03086   0.02268  -0.0799   0.0289   1.0000
   9.500   1.3748   0.03182   0.02376  -0.0788   0.0273   1.0000
   9.750   1.3902   0.03285   0.02486  -0.0774   0.0259   1.0000
  10.000   1.4025   0.03418   0.02624  -0.0758   0.0245   1.0000
  10.250   1.4134   0.03582   0.02801  -0.0740   0.0232   1.0000
  10.500   1.4253   0.03692   0.02932  -0.0722   0.0220   1.0000
  10.750   1.4331   0.03826   0.03085  -0.0700   0.0208   1.0000
  11.000   1.4395   0.03977   0.03253  -0.0679   0.0196   1.0000
  11.250   1.4451   0.04136   0.03425  -0.0661   0.0187   1.0000
  11.500   1.4493   0.04321   0.03618  -0.0647   0.0179   1.0000
  11.750   1.4511   0.04573   0.03882  -0.0632   0.0170   1.0000
  12.000   1.4547   0.04825   0.04165  -0.0619   0.0160   1.0000
  12.250   1.4560   0.05104   0.04471  -0.0608   0.0150   1.0000
  12.500   1.4565   0.05384   0.04771  -0.0601   0.0142   1.0000
  12.750   1.4569   0.05657   0.05060  -0.0599   0.0135   1.0000
  13.000   1.4572   0.05935   0.05349  -0.0600   0.0130   1.0000
  13.250   1.4562   0.06239   0.05663  -0.0603   0.0126   1.0000
  13.500   1.4522   0.06596   0.06032  -0.0607   0.0123   1.0000
  13.750   1.4431   0.07068   0.06535  -0.0610   0.0118   1.0000
  14.000   1.4309   0.07595   0.07092  -0.0617   0.0115   1.0000
  14.250   1.4164   0.08174   0.07701  -0.0630   0.0112   1.0000
  14.500   1.3998   0.08802   0.08354  -0.0649   0.0110   1.0000
  14.750   1.3815   0.09491   0.09068  -0.0674   0.0109   1.0000
  15.000   1.3616   0.10259   0.09857  -0.0709   0.0108   1.0000
  15.250   1.3400   0.11113   0.10734  -0.0752   0.0108   1.0000
  15.500   1.3166   0.12074   0.11717  -0.0806   0.0109   1.0000
  15.750   1.2913   0.13151   0.12815  -0.0871   0.0110   1.0000
  16.000   1.2628   0.14414   0.14097  -0.0951   0.0113   1.0000
  16.250   1.2322   0.15908   0.15604  -0.1047   0.0117   1.0000
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