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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 200,000
Max Cl/Cd: 82.83 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf095-il-200000-n5.txt
Download as CSV file: xf-oaf095-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF095 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7091   0.04718   0.04309  -0.0670   1.0000   0.0225
 -10.250  -0.6922   0.03716   0.03263  -0.0857   1.0000   0.0230
 -10.000  -0.6701   0.03317   0.02833  -0.0922   1.0000   0.0238
  -9.750  -0.6471   0.03004   0.02484  -0.0964   1.0000   0.0248
  -9.500  -0.6232   0.02754   0.02197  -0.0992   1.0000   0.0259
  -9.250  -0.5999   0.02574   0.01997  -0.1008   1.0000   0.0270
  -9.000  -0.5770   0.02466   0.01881  -0.1015   1.0000   0.0282
  -8.750  -0.5517   0.02349   0.01750  -0.1025   0.9993   0.0297
  -8.500  -0.5161   0.02203   0.01577  -0.1055   0.9958   0.0314
  -8.250  -0.4804   0.02068   0.01424  -0.1084   0.9927   0.0332
  -8.000  -0.4453   0.01977   0.01324  -0.1108   0.9888   0.0355
  -7.750  -0.4096   0.01885   0.01215  -0.1132   0.9852   0.0381
  -7.500  -0.3739   0.01786   0.01102  -0.1155   0.9816   0.0405
  -7.250  -0.3397   0.01714   0.01023  -0.1175   0.9766   0.0438
  -7.000  -0.3045   0.01648   0.00942  -0.1194   0.9725   0.0474
  -6.750  -0.2699   0.01574   0.00864  -0.1213   0.9679   0.0513
  -6.500  -0.2368   0.01524   0.00803  -0.1227   0.9621   0.0564
  -6.250  -0.2025   0.01466   0.00742  -0.1243   0.9574   0.0622
  -6.000  -0.1709   0.01427   0.00692  -0.1253   0.9509   0.0690
  -5.750  -0.1391   0.01382   0.00647  -0.1263   0.9447   0.0777
  -5.500  -0.1079   0.01345   0.00607  -0.1271   0.9387   0.0872
  -5.250  -0.0780   0.01314   0.00572  -0.1275   0.9313   0.0980
  -5.000  -0.0480   0.01287   0.00542  -0.1279   0.9253   0.1098
  -4.750  -0.0191   0.01263   0.00516  -0.1281   0.9173   0.1226
  -4.500   0.0099   0.01243   0.00494  -0.1282   0.9110   0.1361
  -4.250   0.0386   0.01224   0.00475  -0.1284   0.9029   0.1501
  -4.000   0.0670   0.01207   0.00456  -0.1283   0.8961   0.1641
  -3.750   0.0957   0.01191   0.00440  -0.1284   0.8881   0.1781
  -3.500   0.1240   0.01177   0.00425  -0.1283   0.8810   0.1921
  -3.250   0.1527   0.01163   0.00412  -0.1284   0.8729   0.2063
  -3.000   0.1809   0.01151   0.00398  -0.1282   0.8654   0.2200
  -2.750   0.2096   0.01140   0.00388  -0.1283   0.8570   0.2340
  -2.500   0.2379   0.01130   0.00377  -0.1281   0.8494   0.2485
  -2.250   0.2668   0.01122   0.00370  -0.1282   0.8413   0.2632
  -2.000   0.2953   0.01115   0.00363  -0.1281   0.8340   0.2788
  -1.750   0.3241   0.01108   0.00359  -0.1281   0.8258   0.2949
  -1.500   0.3526   0.01103   0.00355  -0.1280   0.8183   0.3113
  -1.250   0.3816   0.01099   0.00354  -0.1281   0.8102   0.3286
  -1.000   0.4102   0.01095   0.00352  -0.1280   0.8029   0.3457
  -0.750   0.4391   0.01093   0.00354  -0.1281   0.7948   0.3624
  -0.500   0.4676   0.01091   0.00353  -0.1280   0.7871   0.3783
  -0.250   0.4965   0.01090   0.00356  -0.1280   0.7785   0.3943
   0.000   0.5251   0.01090   0.00358  -0.1279   0.7710   0.4104
   0.250   0.5539   0.01090   0.00364  -0.1280   0.7623   0.4258
   0.500   0.5823   0.01090   0.00367  -0.1278   0.7545   0.4420
   0.750   0.6110   0.01091   0.00374  -0.1278   0.7443   0.4599
   1.000   0.6394   0.01092   0.00380  -0.1277   0.7343   0.4790
   1.250   0.6677   0.01093   0.00387  -0.1275   0.7245   0.4997
   1.500   0.6963   0.01094   0.00397  -0.1275   0.7140   0.5244
   1.750   0.7246   0.01094   0.00408  -0.1274   0.7033   0.5532
   2.000   0.7525   0.01093   0.00417  -0.1272   0.6897   0.5868
   2.250   0.7800   0.01090   0.00426  -0.1268   0.6729   0.6309
   2.500   0.8061   0.01080   0.00436  -0.1261   0.6555   0.7049
   2.750   0.8232   0.01036   0.00430  -0.1230   0.6391   1.0000
   3.000   0.8510   0.01054   0.00439  -0.1228   0.6185   1.0000
   3.250   0.8786   0.01074   0.00450  -0.1226   0.5939   1.0000
   3.500   0.9058   0.01098   0.00464  -0.1222   0.5660   1.0000
   3.750   0.9327   0.01126   0.00481  -0.1219   0.5338   1.0000
   4.000   0.9589   0.01163   0.00501  -0.1215   0.4952   1.0000
   4.250   0.9842   0.01211   0.00527  -0.1210   0.4468   1.0000
   4.500   1.0078   0.01282   0.00565  -0.1203   0.3749   1.0000
   5.000   1.0515   0.01483   0.00682  -0.1189   0.2258   1.0000
   5.250   1.0737   0.01578   0.00748  -0.1183   0.1734   1.0000
   5.500   1.0965   0.01661   0.00810  -0.1177   0.1346   1.0000
   5.750   1.1194   0.01740   0.00873  -0.1170   0.1063   1.0000
   6.000   1.1422   0.01816   0.00938  -0.1164   0.0872   1.0000
   6.250   1.1651   0.01887   0.01005  -0.1157   0.0737   1.0000
   6.750   1.2102   0.02030   0.01146  -0.1141   0.0569   1.0000
   7.000   1.2316   0.02109   0.01225  -0.1131   0.0513   1.0000
   7.250   1.2532   0.02182   0.01305  -0.1122   0.0469   1.0000
   7.500   1.2726   0.02277   0.01398  -0.1110   0.0432   1.0000
   7.750   1.2933   0.02352   0.01482  -0.1099   0.0401   1.0000
   8.000   1.3128   0.02436   0.01571  -0.1087   0.0374   1.0000
   8.250   1.3294   0.02546   0.01683  -0.1072   0.0354   1.0000
   8.500   1.3470   0.02643   0.01790  -0.1057   0.0337   1.0000
   8.750   1.3641   0.02739   0.01896  -0.1042   0.0319   1.0000
   9.000   1.3804   0.02836   0.01999  -0.1026   0.0303   1.0000
   9.250   1.3941   0.02951   0.02117  -0.1007   0.0289   1.0000
   9.500   1.4057   0.03082   0.02257  -0.0986   0.0279   1.0000
   9.750   1.4168   0.03201   0.02389  -0.0962   0.0270   1.0000
  10.000   1.4274   0.03329   0.02529  -0.0939   0.0261   1.0000
  10.250   1.4379   0.03460   0.02671  -0.0918   0.0251   1.0000
  10.500   1.4479   0.03594   0.02813  -0.0899   0.0243   1.0000
  10.750   1.4567   0.03738   0.02964  -0.0879   0.0235   1.0000
  11.000   1.4633   0.03919   0.03151  -0.0859   0.0228   1.0000
  11.250   1.4719   0.04089   0.03338  -0.0841   0.0222   1.0000
  11.500   1.4795   0.04276   0.03545  -0.0823   0.0216   1.0000
  11.750   1.4858   0.04476   0.03763  -0.0805   0.0210   1.0000
  12.000   1.4910   0.04689   0.03993  -0.0788   0.0205   1.0000
  12.250   1.4950   0.04913   0.04233  -0.0773   0.0201   1.0000
  12.500   1.4978   0.05146   0.04481  -0.0759   0.0196   1.0000
  12.750   1.4998   0.05390   0.04738  -0.0747   0.0192   1.0000
  13.000   1.5007   0.05646   0.05008  -0.0737   0.0189   1.0000
  13.250   1.5004   0.05924   0.05296  -0.0728   0.0185   1.0000
  13.500   1.4979   0.06245   0.05628  -0.0721   0.0182   1.0000
  13.750   1.4919   0.06621   0.06028  -0.0716   0.0179   1.0000
  14.000   1.4839   0.07037   0.06472  -0.0715   0.0176   1.0000
  14.250   1.4737   0.07498   0.06959  -0.0719   0.0174   1.0000
  14.500   1.4614   0.08005   0.07491  -0.0727   0.0172   1.0000
  14.750   1.4472   0.08565   0.08075  -0.0741   0.0170   1.0000
  15.000   1.4313   0.09190   0.08726  -0.0762   0.0169   1.0000
  15.250   1.4135   0.09886   0.09445  -0.0791   0.0168   1.0000
  15.500   1.3935   0.10671   0.10255  -0.0830   0.0167   1.0000
  15.750   1.3710   0.11570   0.11178  -0.0881   0.0167   1.0000
  16.000   1.3448   0.12627   0.12260  -0.0947   0.0168   1.0000
  16.250   1.3120   0.13972   0.13631  -0.1038   0.0169   1.0000
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