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OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: OAF102 AIRFOIL (oaf102-il)
Reynolds number: 50,000
Max Cl/Cd: 41.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf102-il-50000-n5.txt
Download as CSV file: xf-oaf102-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF102 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4822   0.09828   0.09108  -0.0305   1.0000   0.0613
  -9.250  -0.4878   0.09241   0.08530  -0.0342   1.0000   0.0616
  -9.000  -0.4960   0.08606   0.07905  -0.0383   1.0000   0.0619
  -8.750  -0.5068   0.07892   0.07201  -0.0434   1.0000   0.0621
  -8.500  -0.5168   0.06951   0.06262  -0.0529   1.0000   0.0621
  -8.250  -0.5237   0.05777   0.05064  -0.0682   1.0000   0.0621
  -8.000  -0.5110   0.05446   0.04731  -0.0706   1.0000   0.0642
  -7.750  -0.4979   0.04855   0.04108  -0.0771   1.0000   0.0661
  -7.500  -0.4786   0.04315   0.03521  -0.0828   1.0000   0.0690
  -7.250  -0.4525   0.03770   0.02887  -0.0889   1.0000   0.0745
  -7.000  -0.4316   0.03607   0.02730  -0.0892   1.0000   0.0789
  -6.750  -0.4066   0.03340   0.02419  -0.0910   1.0000   0.0850
  -6.500  -0.3837   0.03178   0.02244  -0.0917   1.0000   0.0922
  -6.250  -0.3585   0.02982   0.02008  -0.0927   1.0000   0.1011
  -6.000  -0.3361   0.02876   0.01901  -0.0929   1.0000   0.1116
  -5.750  -0.3128   0.02765   0.01783  -0.0933   1.0000   0.1234
  -5.500  -0.2890   0.02674   0.01683  -0.0937   1.0000   0.1394
  -5.250  -0.2649   0.02598   0.01595  -0.0941   1.0000   0.1579
  -5.000  -0.2417   0.02554   0.01553  -0.0942   1.0000   0.1780
  -4.750  -0.2179   0.02512   0.01499  -0.0945   1.0000   0.2020
  -4.500  -0.1912   0.02491   0.01481  -0.0952   0.9982   0.2257
  -4.250  -0.1524   0.02466   0.01447  -0.0980   0.9913   0.2545
  -4.000  -0.1134   0.02448   0.01420  -0.1008   0.9846   0.2817
  -3.750  -0.0752   0.02430   0.01385  -0.1033   0.9773   0.3075
  -3.500  -0.0360   0.02418   0.01367  -0.1059   0.9712   0.3302
  -3.250   0.0009   0.02403   0.01338  -0.1081   0.9635   0.3531
  -3.000   0.0402   0.02391   0.01319  -0.1106   0.9576   0.3740
  -2.750   0.0762   0.02380   0.01298  -0.1126   0.9499   0.3950
  -2.500   0.1156   0.02365   0.01275  -0.1151   0.9438   0.4164
  -2.250   0.1503   0.02358   0.01262  -0.1167   0.9361   0.4360
  -2.000   0.1875   0.02347   0.01243  -0.1187   0.9293   0.4573
  -1.750   0.2212   0.02341   0.01231  -0.1201   0.9213   0.4765
  -1.500   0.2563   0.02331   0.01220  -0.1216   0.9142   0.4957
  -1.250   0.2879   0.02329   0.01216  -0.1225   0.9057   0.5150
  -1.000   0.3225   0.02322   0.01207  -0.1239   0.8985   0.5366
  -0.750   0.3517   0.02323   0.01213  -0.1243   0.8896   0.5566
  -0.500   0.3851   0.02315   0.01209  -0.1252   0.8826   0.5806
  -0.250   0.4121   0.02320   0.01223  -0.1252   0.8733   0.6033
   0.000   0.4441   0.02310   0.01224  -0.1257   0.8666   0.6304
   0.250   0.4694   0.02318   0.01246  -0.1254   0.8571   0.6585
   0.500   0.4989   0.02304   0.01250  -0.1253   0.8508   0.6931
   0.750   0.5201   0.02309   0.01279  -0.1240   0.8411   0.7366
   1.000   0.5412   0.02281   0.01281  -0.1219   0.8342   0.8179
   1.250   0.5650   0.02290   0.01297  -0.1213   0.8242   1.0000
   1.500   0.5973   0.02325   0.01325  -0.1225   0.8166   1.0000
   1.750   0.6279   0.02362   0.01357  -0.1233   0.8084   1.0000
   2.000   0.6571   0.02403   0.01397  -0.1238   0.8000   1.0000
   2.250   0.6874   0.02435   0.01432  -0.1242   0.7922   1.0000
   2.500   0.7145   0.02484   0.01485  -0.1244   0.7830   1.0000
   2.750   0.7452   0.02512   0.01516  -0.1247   0.7759   1.0000
   3.000   0.7707   0.02570   0.01583  -0.1246   0.7659   1.0000
   3.250   0.8019   0.02590   0.01614  -0.1247   0.7595   1.0000
   3.500   0.8261   0.02656   0.01693  -0.1245   0.7486   1.0000
   3.750   0.8532   0.02702   0.01753  -0.1243   0.7398   1.0000
   4.000   0.8814   0.02738   0.01807  -0.1241   0.7311   1.0000
   4.250   0.9060   0.02799   0.01886  -0.1237   0.7203   1.0000
   4.500   0.9341   0.02829   0.01935  -0.1232   0.7111   1.0000
   4.750   0.9612   0.02823   0.01949  -0.1220   0.6966   1.0000
   5.000   0.9862   0.02698   0.01834  -0.1183   0.6645   1.0000
   5.250   1.0075   0.02563   0.01697  -0.1138   0.6181   1.0000
   5.500   1.0276   0.02520   0.01661  -0.1108   0.5718   1.0000
   5.750   1.0471   0.02511   0.01656  -0.1081   0.5134   1.0000
   6.000   1.0626   0.02545   0.01638  -0.1045   0.3924   1.0000
   6.250   1.0612   0.02826   0.01769  -0.1005   0.2101   1.0000
   6.500   1.0647   0.03110   0.01988  -0.0980   0.1460   1.0000
   6.750   1.0725   0.03336   0.02188  -0.0959   0.1212   1.0000
   7.000   1.0823   0.03532   0.02379  -0.0937   0.1064   1.0000
   7.250   1.0929   0.03716   0.02564  -0.0917   0.0954   1.0000
   7.500   1.1066   0.03885   0.02747  -0.0897   0.0876   1.0000
   7.750   1.1208   0.04065   0.02918  -0.0879   0.0808   1.0000
   8.000   1.1432   0.04210   0.03088  -0.0867   0.0738   1.0000
   8.250   1.1700   0.04386   0.03255  -0.0860   0.0689   1.0000
   8.500   1.1996   0.04569   0.03466  -0.0855   0.0636   1.0000
   8.750   1.2261   0.04773   0.03685  -0.0850   0.0593   1.0000
   9.000   1.2552   0.05034   0.03947  -0.0850   0.0567   1.0000
   9.250   1.2769   0.05322   0.04274  -0.0841   0.0542   1.0000
   9.500   1.2918   0.05608   0.04605  -0.0826   0.0516   1.0000
   9.750   1.3045   0.05908   0.04940  -0.0811   0.0496   1.0000
  10.000   1.3147   0.06242   0.05312  -0.0795   0.0484   1.0000
  10.250   1.3210   0.06589   0.05691  -0.0777   0.0476   1.0000
  10.500   1.3230   0.06940   0.06071  -0.0758   0.0468   1.0000
  10.750   1.3226   0.07292   0.06446  -0.0738   0.0460   1.0000
  11.000   1.3198   0.07688   0.06854  -0.0720   0.0452   1.0000
  11.250   1.3014   0.08049   0.07251  -0.0690   0.0449   1.0000
  11.500   1.2820   0.08465   0.07700  -0.0671   0.0448   1.0000
  11.750   1.2615   0.08933   0.08197  -0.0662   0.0447   1.0000
  12.000   1.2400   0.09456   0.08746  -0.0664   0.0447   1.0000
  12.250   1.2182   0.10034   0.09348  -0.0676   0.0447   1.0000
  12.500   1.1963   0.10670   0.10004  -0.0698   0.0448   1.0000
  12.750   1.1749   0.11363   0.10715  -0.0729   0.0450   1.0000
  13.000   1.1544   0.12113   0.11479  -0.0769   0.0451   1.0000
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