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OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: OAF102 AIRFOIL (oaf102-il)
Reynolds number: 500,000
Max Cl/Cd: 107.16 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf102-il-500000.txt
Download as CSV file: xf-oaf102-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7502   0.06818   0.06561  -0.0349   1.0000   0.0159
 -11.250  -0.7812   0.05789   0.05520  -0.0436   1.0000   0.0157
 -11.000  -0.8013   0.04827   0.04541  -0.0547   1.0000   0.0156
 -10.750  -0.7891   0.03718   0.03384  -0.0758   1.0000   0.0157
 -10.500  -0.7678   0.03286   0.02912  -0.0828   1.0000   0.0159
 -10.250  -0.7478   0.02740   0.02319  -0.0887   1.0000   0.0163
 -10.000  -0.7217   0.02510   0.02074  -0.0913   1.0000   0.0169
  -9.750  -0.6938   0.02365   0.01917  -0.0931   1.0000   0.0175
  -9.500  -0.6650   0.02228   0.01764  -0.0948   1.0000   0.0182
  -9.250  -0.6357   0.02097   0.01617  -0.0964   1.0000   0.0191
  -9.000  -0.6058   0.01985   0.01487  -0.0979   1.0000   0.0199
  -8.750  -0.5755   0.01820   0.01304  -0.0997   1.0000   0.0211
  -8.500  -0.5453   0.01726   0.01206  -0.1012   1.0000   0.0225
  -8.250  -0.5150   0.01659   0.01133  -0.1024   1.0000   0.0239
  -8.000  -0.4848   0.01591   0.01055  -0.1034   1.0000   0.0253
  -7.750  -0.4510   0.01469   0.00922  -0.1056   0.9954   0.0273
  -7.500  -0.4149   0.01405   0.00854  -0.1079   0.9869   0.0296
  -7.250  -0.3802   0.01365   0.00805  -0.1096   0.9776   0.0322
  -7.000  -0.3469   0.01281   0.00714  -0.1112   0.9676   0.0358
  -6.750  -0.3184   0.01248   0.00675  -0.1114   0.9558   0.0391
  -6.500  -0.2908   0.01204   0.00621  -0.1114   0.9437   0.0434
  -6.250  -0.2632   0.01169   0.00582  -0.1114   0.9322   0.0489
  -6.000  -0.2349   0.01127   0.00536  -0.1116   0.9219   0.0562
  -5.750  -0.2070   0.01095   0.00499  -0.1116   0.9120   0.0662
  -5.500  -0.1777   0.01058   0.00464  -0.1120   0.9015   0.0813
  -5.250  -0.1488   0.01030   0.00437  -0.1122   0.8920   0.1008
  -5.000  -0.1198   0.01001   0.00411  -0.1125   0.8826   0.1239
  -4.750  -0.0903   0.00978   0.00390  -0.1129   0.8728   0.1457
  -4.500  -0.0614   0.00962   0.00376  -0.1131   0.8640   0.1688
  -4.250  -0.0320   0.00949   0.00362  -0.1134   0.8545   0.1879
  -4.000  -0.0027   0.00937   0.00348  -0.1137   0.8453   0.2051
  -3.750   0.0264   0.00927   0.00336  -0.1138   0.8362   0.2214
  -3.500   0.0560   0.00917   0.00326  -0.1142   0.8268   0.2373
  -3.250   0.0853   0.00911   0.00316  -0.1144   0.8187   0.2529
  -3.000   0.1150   0.00903   0.00309  -0.1147   0.8102   0.2689
  -2.750   0.1444   0.00898   0.00303  -0.1150   0.8029   0.2851
  -2.500   0.1741   0.00892   0.00297  -0.1153   0.7951   0.3013
  -2.250   0.2036   0.00890   0.00293  -0.1156   0.7886   0.3173
  -2.000   0.2334   0.00885   0.00290  -0.1159   0.7812   0.3329
  -1.750   0.2627   0.00885   0.00288  -0.1161   0.7749   0.3482
  -1.500   0.2925   0.00882   0.00287  -0.1165   0.7677   0.3631
  -1.250   0.3219   0.00882   0.00286  -0.1167   0.7613   0.3775
  -1.000   0.3516   0.00881   0.00288  -0.1170   0.7549   0.3916
  -0.750   0.3812   0.00881   0.00289  -0.1173   0.7485   0.4052
  -0.500   0.4106   0.00883   0.00291  -0.1175   0.7424   0.4188
  -0.250   0.4402   0.00882   0.00293  -0.1178   0.7352   0.4329
   0.000   0.4694   0.00887   0.00296  -0.1180   0.7292   0.4467
   0.250   0.4991   0.00886   0.00300  -0.1183   0.7224   0.4596
   0.500   0.5285   0.00887   0.00304  -0.1185   0.7164   0.4720
   0.750   0.5580   0.00889   0.00309  -0.1188   0.7103   0.4848
   1.000   0.5876   0.00889   0.00315  -0.1191   0.7038   0.4982
   1.250   0.6168   0.00894   0.00321  -0.1193   0.6981   0.5125
   1.500   0.6464   0.00892   0.00329  -0.1196   0.6913   0.5287
   1.750   0.6757   0.00895   0.00336  -0.1198   0.6852   0.5469
   2.000   0.7053   0.00896   0.00347  -0.1201   0.6787   0.5675
   2.250   0.7347   0.00894   0.00356  -0.1204   0.6719   0.5922
   2.750   0.7924   0.00872   0.00365  -0.1206   0.6415   0.6967
   3.000   0.8106   0.00806   0.00351  -0.1179   0.6226   1.0000
   3.250   0.8397   0.00815   0.00355  -0.1181   0.6027   1.0000
   3.500   0.8687   0.00827   0.00364  -0.1182   0.5849   1.0000
   3.750   0.8974   0.00844   0.00375  -0.1184   0.5636   1.0000
   4.000   0.9259   0.00864   0.00387  -0.1185   0.5353   1.0000
   4.250   0.9539   0.00897   0.00404  -0.1185   0.4927   1.0000
   4.500   0.9807   0.00956   0.00433  -0.1185   0.4274   1.0000
   4.750   1.0038   0.01106   0.00502  -0.1185   0.2705   1.0000
   5.000   1.0250   0.01289   0.00599  -0.1183   0.1181   1.0000
   5.250   1.0497   0.01382   0.00662  -0.1181   0.0707   1.0000
   5.500   1.0754   0.01447   0.00719  -0.1179   0.0546   1.0000
   5.750   1.1006   0.01517   0.00784  -0.1176   0.0451   1.0000
   6.000   1.1270   0.01559   0.00830  -0.1174   0.0410   1.0000
   6.250   1.1505   0.01647   0.00917  -0.1168   0.0359   1.0000
   6.500   1.1761   0.01693   0.00968  -0.1164   0.0336   1.0000
   6.750   1.2009   0.01747   0.01024  -0.1160   0.0310   1.0000
   7.000   1.2217   0.01856   0.01134  -0.1150   0.0284   1.0000
   7.250   1.2444   0.01931   0.01216  -0.1142   0.0272   1.0000
   7.500   1.2674   0.01997   0.01289  -0.1135   0.0257   1.0000
   7.750   1.2899   0.02064   0.01358  -0.1127   0.0243   1.0000
   8.000   1.3106   0.02147   0.01442  -0.1118   0.0229   1.0000
   8.250   1.3246   0.02321   0.01623  -0.1097   0.0217   1.0000
   8.500   1.3457   0.02396   0.01706  -0.1087   0.0211   1.0000
   8.750   1.3651   0.02489   0.01808  -0.1074   0.0203   1.0000
   9.000   1.3836   0.02589   0.01916  -0.1060   0.0196   1.0000
   9.250   1.4014   0.02691   0.02024  -0.1046   0.0189   1.0000
   9.500   1.4185   0.02789   0.02126  -0.1031   0.0183   1.0000
   9.750   1.4335   0.02911   0.02251  -0.1014   0.0176   1.0000
  10.000   1.4462   0.03167   0.02520  -0.0995   0.0168   1.0000
  10.250   1.4609   0.03266   0.02635  -0.0976   0.0165   1.0000
  10.500   1.4742   0.03404   0.02788  -0.0956   0.0161   1.0000
  10.750   1.4858   0.03560   0.02960  -0.0935   0.0156   1.0000
  11.000   1.4939   0.03727   0.03143  -0.0909   0.0153   1.0000
  11.250   1.5004   0.03905   0.03337  -0.0883   0.0150   1.0000
  11.500   1.5057   0.04093   0.03540  -0.0858   0.0147   1.0000
  11.750   1.5099   0.04288   0.03749  -0.0834   0.0144   1.0000
  12.000   1.5121   0.04502   0.03979  -0.0812   0.0142   1.0000
  12.250   1.5130   0.04732   0.04226  -0.0791   0.0140   1.0000
  12.500   1.5125   0.04975   0.04483  -0.0772   0.0138   1.0000
  12.750   1.5116   0.05228   0.04747  -0.0756   0.0136   1.0000
  13.000   1.5072   0.05545   0.05078  -0.0741   0.0133   1.0000
  13.250   1.4953   0.05982   0.05538  -0.0725   0.0132   1.0000
  13.500   1.4754   0.06536   0.06118  -0.0714   0.0130   1.0000
  14.000   1.4298   0.07744   0.07379  -0.0715   0.0129   1.0000
  14.250   1.4121   0.08303   0.07960  -0.0727   0.0129   1.0000
  14.500   1.3911   0.08956   0.08634  -0.0746   0.0129   1.0000
  14.750   1.3678   0.09698   0.09397  -0.0774   0.0129   1.0000
  15.000   1.3431   0.10539   0.10258  -0.0813   0.0129   1.0000
  15.250   1.3180   0.11464   0.11202  -0.0862   0.0130   1.0000
  15.500   1.2995   0.12332   0.12087  -0.0917   0.0130   1.0000
  15.750   1.2818   0.13273   0.13044  -0.0980   0.0131   1.0000
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