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OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: OAF102 AIRFOIL (oaf102-il)
Reynolds number: 200,000
Max Cl/Cd: 77.44 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf102-il-200000-n5.txt
Download as CSV file: xf-oaf102-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7015   0.06522   0.06152  -0.0398   1.0000   0.0182
 -10.500  -0.7414   0.05124   0.04729  -0.0546   1.0000   0.0176
 -10.250  -0.7334   0.04048   0.03607  -0.0737   1.0000   0.0179
 -10.000  -0.7136   0.03565   0.03082  -0.0813   1.0000   0.0186
  -9.750  -0.6906   0.03201   0.02673  -0.0860   1.0000   0.0193
  -9.500  -0.6650   0.02916   0.02348  -0.0893   1.0000   0.0201
  -9.250  -0.6386   0.02688   0.02096  -0.0917   1.0000   0.0208
  -9.000  -0.6110   0.02535   0.01932  -0.0936   1.0000   0.0217
  -8.750  -0.5827   0.02411   0.01795  -0.0952   1.0000   0.0231
  -8.500  -0.5540   0.02287   0.01649  -0.0967   1.0000   0.0248
  -8.250  -0.5251   0.02156   0.01499  -0.0981   1.0000   0.0264
  -8.000  -0.4965   0.02044   0.01381  -0.0995   1.0000   0.0279
  -7.750  -0.4654   0.01952   0.01279  -0.1011   0.9950   0.0300
  -7.500  -0.4299   0.01870   0.01177  -0.1034   0.9853   0.0328
  -7.250  -0.3945   0.01767   0.01069  -0.1059   0.9767   0.0360
  -7.000  -0.3594   0.01695   0.00983  -0.1080   0.9680   0.0395
  -6.750  -0.3253   0.01620   0.00901  -0.1098   0.9586   0.0442
  -6.500  -0.2930   0.01565   0.00834  -0.1111   0.9486   0.0495
  -6.250  -0.2613   0.01507   0.00771  -0.1123   0.9388   0.0564
  -6.000  -0.2311   0.01461   0.00718  -0.1130   0.9285   0.0650
  -5.750  -0.2014   0.01418   0.00670  -0.1135   0.9181   0.0761
  -5.500  -0.1722   0.01379   0.00630  -0.1140   0.9084   0.0911
  -5.250  -0.1434   0.01344   0.00595  -0.1143   0.8986   0.1091
  -5.000  -0.1144   0.01315   0.00563  -0.1146   0.8888   0.1289
  -4.750  -0.0858   0.01289   0.00539  -0.1148   0.8799   0.1500
  -4.500  -0.0569   0.01270   0.00518  -0.1151   0.8704   0.1715
  -4.250  -0.0281   0.01253   0.00499  -0.1152   0.8617   0.1907
  -4.000   0.0006   0.01238   0.00481  -0.1154   0.8530   0.2090
  -3.750   0.0297   0.01225   0.00466  -0.1156   0.8444   0.2267
  -3.500   0.0583   0.01215   0.00452  -0.1157   0.8364   0.2437
  -3.250   0.0876   0.01205   0.00440  -0.1159   0.8278   0.2602
  -3.000   0.1163   0.01198   0.00428  -0.1160   0.8204   0.2761
  -2.750   0.1458   0.01190   0.00420  -0.1163   0.8118   0.2914
  -2.500   0.1746   0.01185   0.00410  -0.1163   0.8041   0.3066
  -2.000   0.2328   0.01177   0.00399  -0.1167   0.7881   0.3366
  -1.750   0.2622   0.01173   0.00395  -0.1169   0.7804   0.3517
  -1.500   0.2912   0.01172   0.00392  -0.1170   0.7741   0.3664
  -1.250   0.3207   0.01170   0.00393  -0.1173   0.7666   0.3813
  -1.000   0.3498   0.01171   0.00392  -0.1175   0.7604   0.3960
  -0.750   0.3793   0.01170   0.00395  -0.1177   0.7538   0.4102
  -0.500   0.4085   0.01170   0.00396  -0.1179   0.7474   0.4230
  -0.250   0.4377   0.01172   0.00399  -0.1181   0.7412   0.4352
   0.000   0.4670   0.01173   0.00403  -0.1183   0.7344   0.4476
   0.250   0.4960   0.01176   0.00406  -0.1184   0.7290   0.4611
   0.500   0.5254   0.01177   0.00415  -0.1187   0.7218   0.4751
   0.750   0.5543   0.01180   0.00420  -0.1188   0.7154   0.4889
   1.000   0.5835   0.01182   0.00429  -0.1190   0.7083   0.5029
   1.250   0.6125   0.01185   0.00439  -0.1192   0.7016   0.5192
   1.500   0.6415   0.01187   0.00450  -0.1193   0.6952   0.5383
   1.750   0.6706   0.01188   0.00463  -0.1195   0.6882   0.5604
   2.000   0.6994   0.01190   0.00476  -0.1196   0.6821   0.5843
   2.250   0.7284   0.01190   0.00493  -0.1198   0.6747   0.6128
   2.500   0.7566   0.01188   0.00506  -0.1197   0.6686   0.6506
   2.750   0.7841   0.01178   0.00525  -0.1195   0.6608   0.7149
   3.000   0.8014   0.01126   0.00515  -0.1165   0.6543   1.0000
   3.250   0.8304   0.01137   0.00527  -0.1166   0.6413   1.0000
   3.500   0.8582   0.01145   0.00528  -0.1164   0.6156   1.0000
   3.750   0.8853   0.01158   0.00527  -0.1160   0.5789   1.0000
   4.000   0.9125   0.01180   0.00536  -0.1157   0.5378   1.0000
   4.250   0.9394   0.01213   0.00552  -0.1155   0.4942   1.0000
   4.500   0.9650   0.01269   0.00579  -0.1152   0.4322   1.0000
   4.750   0.9871   0.01385   0.00635  -0.1147   0.3143   1.0000
   5.000   1.0058   0.01571   0.00736  -0.1141   0.1678   1.0000
   5.250   1.0277   0.01694   0.00820  -0.1137   0.1007   1.0000
   5.500   1.0514   0.01780   0.00890  -0.1133   0.0733   1.0000
   5.750   1.0755   0.01855   0.00960  -0.1129   0.0597   1.0000
   6.000   1.0994   0.01925   0.01032  -0.1124   0.0512   1.0000
   6.250   1.1222   0.02008   0.01111  -0.1118   0.0448   1.0000
   6.500   1.1456   0.02077   0.01189  -0.1111   0.0408   1.0000
   6.750   1.1675   0.02161   0.01276  -0.1104   0.0373   1.0000
   7.000   1.1883   0.02253   0.01372  -0.1094   0.0344   1.0000
   7.250   1.2096   0.02334   0.01461  -0.1085   0.0318   1.0000
   7.500   1.2294   0.02426   0.01558  -0.1074   0.0299   1.0000
   7.750   1.2463   0.02549   0.01683  -0.1060   0.0283   1.0000
   8.000   1.2645   0.02653   0.01797  -0.1046   0.0269   1.0000
   8.250   1.2828   0.02752   0.01906  -0.1033   0.0254   1.0000
   8.500   1.3001   0.02854   0.02015  -0.1019   0.0240   1.0000
   8.750   1.3160   0.02967   0.02133  -0.1003   0.0230   1.0000
   9.000   1.3295   0.03104   0.02275  -0.0984   0.0222   1.0000
   9.250   1.3431   0.03257   0.02437  -0.0965   0.0215   1.0000
   9.500   1.3580   0.03392   0.02588  -0.0948   0.0208   1.0000
   9.750   1.3719   0.03528   0.02740  -0.0930   0.0199   1.0000
  10.000   1.3831   0.03660   0.02885  -0.0908   0.0190   1.0000
  10.250   1.3934   0.03795   0.03031  -0.0887   0.0183   1.0000
  10.500   1.4030   0.03942   0.03186  -0.0868   0.0178   1.0000
  10.750   1.4122   0.04113   0.03368  -0.0849   0.0174   1.0000
  11.000   1.4206   0.04327   0.03592  -0.0831   0.0169   1.0000
  11.250   1.4281   0.04548   0.03837  -0.0811   0.0166   1.0000
  11.500   1.4333   0.04793   0.04111  -0.0792   0.0163   1.0000
  11.750   1.4358   0.05068   0.04414  -0.0772   0.0159   1.0000
  12.000   1.4351   0.05370   0.04745  -0.0753   0.0156   1.0000
  12.250   1.4319   0.05694   0.05097  -0.0736   0.0153   1.0000
  12.500   1.4265   0.06040   0.05469  -0.0722   0.0150   1.0000
  12.750   1.4197   0.06403   0.05857  -0.0712   0.0147   1.0000
  13.000   1.4114   0.06791   0.06267  -0.0706   0.0145   1.0000
  13.250   1.4015   0.07211   0.06709  -0.0705   0.0142   1.0000
  13.500   1.3901   0.07668   0.07187  -0.0707   0.0141   1.0000
  13.750   1.3771   0.08163   0.07703  -0.0715   0.0139   1.0000
  14.000   1.3629   0.08703   0.08262  -0.0729   0.0138   1.0000
  14.250   1.3448   0.09340   0.08922  -0.0750   0.0137   1.0000
  14.500   1.3239   0.10077   0.09682  -0.0781   0.0137   1.0000
  14.750   1.2967   0.11023   0.10655  -0.0831   0.0137   1.0000
  15.000   1.2402   0.12856   0.12533  -0.0948   0.0141   1.0000
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