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OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: OAF128 AIRFOIL (oaf128-il)
Reynolds number: 200,000
Max Cl/Cd: 56.54 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf128-il-200000.txt
Download as CSV file: xf-oaf128-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF128 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.9756   0.09273   0.08858   0.0091   1.0000   0.0432
 -13.250  -1.0120   0.08173   0.07740   0.0010   1.0000   0.0427
 -13.000  -1.0457   0.07185   0.06730  -0.0070   1.0000   0.0424
 -12.750  -1.0739   0.06359   0.05878  -0.0139   1.0000   0.0421
 -12.500  -1.0970   0.05707   0.05199  -0.0191   1.0000   0.0420
 -12.250  -1.1165   0.05232   0.04697  -0.0214   1.0000   0.0420
 -12.000  -1.1250   0.04839   0.04272  -0.0222   1.0000   0.0421
 -11.750  -1.1251   0.04492   0.03889  -0.0226   1.0000   0.0425
 -11.500  -1.1193   0.04190   0.03545  -0.0228   1.0000   0.0430
 -11.250  -1.1079   0.03915   0.03233  -0.0229   1.0000   0.0436
 -11.000  -1.0885   0.03688   0.03006  -0.0229   1.0000   0.0445
 -10.750  -1.0684   0.03509   0.02819  -0.0228   1.0000   0.0453
 -10.500  -1.0475   0.03333   0.02630  -0.0228   1.0000   0.0462
 -10.250  -1.0257   0.03161   0.02440  -0.0227   1.0000   0.0473
 -10.000  -1.0029   0.02998   0.02254  -0.0227   1.0000   0.0484
  -9.750  -0.9795   0.02834   0.02074  -0.0227   1.0000   0.0496
  -9.500  -0.9553   0.02697   0.01946  -0.0227   1.0000   0.0512
  -9.250  -0.9301   0.02584   0.01828  -0.0227   1.0000   0.0532
  -9.000  -0.9041   0.02474   0.01701  -0.0228   1.0000   0.0553
  -8.750  -0.8792   0.02335   0.01572  -0.0229   1.0000   0.0574
  -8.500  -0.8527   0.02234   0.01470  -0.0230   1.0000   0.0602
  -8.250  -0.8260   0.02125   0.01356  -0.0233   1.0000   0.0636
  -8.000  -0.7986   0.02036   0.01271  -0.0236   1.0000   0.0681
  -7.750  -0.7710   0.01937   0.01175  -0.0240   1.0000   0.0736
  -7.500  -0.7427   0.01846   0.01086  -0.0244   1.0000   0.0815
  -7.250  -0.7140   0.01762   0.01010  -0.0250   1.0000   0.0936
  -7.000  -0.6848   0.01684   0.00935  -0.0255   1.0000   0.1117
  -6.750  -0.6556   0.01610   0.00873  -0.0262   1.0000   0.1305
  -6.500  -0.6258   0.01560   0.00826  -0.0268   1.0000   0.1480
  -6.250  -0.5959   0.01522   0.00790  -0.0273   1.0000   0.1637
  -6.000  -0.5658   0.01489   0.00758  -0.0278   1.0000   0.1786
  -5.750  -0.5356   0.01452   0.00724  -0.0283   1.0000   0.1934
  -5.500  -0.5054   0.01410   0.00688  -0.0289   1.0000   0.2088
  -5.250  -0.4751   0.01369   0.00655  -0.0295   1.0000   0.2254
  -5.000  -0.4445   0.01338   0.00630  -0.0301   1.0000   0.2445
  -4.750  -0.4137   0.01310   0.00611  -0.0308   1.0000   0.2650
  -4.500  -0.3828   0.01283   0.00595  -0.0314   1.0000   0.2844
  -4.250  -0.3515   0.01257   0.00577  -0.0322   1.0000   0.3023
  -4.000  -0.3198   0.01234   0.00561  -0.0330   1.0000   0.3202
  -3.750  -0.2877   0.01212   0.00548  -0.0340   1.0000   0.3380
  -3.500  -0.2511   0.01204   0.00547  -0.0359   0.9703   0.3569
  -3.250  -0.2191   0.01213   0.00555  -0.0362   0.9264   0.3748
  -3.000  -0.1962   0.01225   0.00561  -0.0344   0.8904   0.3905
  -2.750  -0.1723   0.01232   0.00559  -0.0329   0.8587   0.4064
  -2.500  -0.1472   0.01232   0.00556  -0.0318   0.8304   0.4217
  -2.250  -0.1209   0.01231   0.00550  -0.0309   0.8033   0.4364
  -2.000  -0.0938   0.01231   0.00543  -0.0302   0.7785   0.4514
  -1.750  -0.0655   0.01230   0.00535  -0.0299   0.7540   0.4669
  -1.500  -0.0370   0.01232   0.00530  -0.0296   0.7314   0.4836
  -1.250  -0.0083   0.01234   0.00526  -0.0293   0.7098   0.5013
  -1.000   0.0205   0.01233   0.00521  -0.0291   0.6887   0.5175
  -0.750   0.0494   0.01231   0.00515  -0.0290   0.6681   0.5326
  -0.500   0.0785   0.01230   0.00510  -0.0289   0.6484   0.5487
  -0.250   0.1080   0.01228   0.00507  -0.0289   0.6308   0.5656
   0.000   0.1376   0.01227   0.00507  -0.0289   0.6147   0.5833
   0.250   0.1670   0.01226   0.00507  -0.0289   0.5993   0.6026
   0.500   0.1962   0.01227   0.00509  -0.0289   0.5850   0.6243
   0.750   0.2254   0.01228   0.00513  -0.0288   0.5713   0.6498
   1.000   0.2544   0.01224   0.00521  -0.0287   0.5573   0.6780
   1.250   0.2828   0.01223   0.00529  -0.0284   0.5441   0.7112
   1.500   0.3100   0.01224   0.00536  -0.0278   0.5319   0.7487
   1.750   0.3360   0.01216   0.00546  -0.0269   0.5190   0.7924
   2.000   0.3594   0.01210   0.00551  -0.0252   0.5074   0.8437
   2.250   0.3786   0.01192   0.00540  -0.0225   0.4963   0.9075
   2.500   0.4079   0.01171   0.00522  -0.0224   0.4830   1.0000
   2.750   0.4398   0.01192   0.00532  -0.0232   0.4704   1.0000
   3.000   0.4709   0.01213   0.00539  -0.0238   0.4566   1.0000
   3.250   0.5017   0.01227   0.00544  -0.0242   0.4400   1.0000
   3.500   0.5323   0.01241   0.00551  -0.0247   0.4232   1.0000
   3.750   0.5628   0.01257   0.00564  -0.0251   0.4078   1.0000
   4.000   0.5932   0.01277   0.00578  -0.0255   0.3926   1.0000
   4.250   0.6233   0.01298   0.00593  -0.0258   0.3777   1.0000
   4.500   0.6532   0.01320   0.00609  -0.0261   0.3626   1.0000
   4.750   0.6830   0.01344   0.00625  -0.0264   0.3474   1.0000
   5.000   0.7126   0.01370   0.00644  -0.0267   0.3320   1.0000
   5.250   0.7422   0.01395   0.00665  -0.0270   0.3159   1.0000
   5.500   0.7716   0.01422   0.00689  -0.0273   0.2994   1.0000
   5.750   0.8008   0.01452   0.00715  -0.0275   0.2823   1.0000
   6.000   0.8299   0.01485   0.00743  -0.0278   0.2640   1.0000
   6.250   0.8588   0.01521   0.00776  -0.0280   0.2437   1.0000
   6.500   0.8871   0.01569   0.00816  -0.0283   0.2214   1.0000
   6.750   0.9148   0.01632   0.00865  -0.0285   0.1986   1.0000
   7.000   0.9427   0.01693   0.00920  -0.0287   0.1762   1.0000
   7.250   0.9700   0.01762   0.00978  -0.0289   0.1590   1.0000
   7.500   0.9969   0.01835   0.01044  -0.0290   0.1462   1.0000
   7.750   1.0233   0.01915   0.01118  -0.0290   0.1364   1.0000
   8.000   1.0488   0.02003   0.01196  -0.0290   0.1285   1.0000
   8.250   1.0751   0.02076   0.01274  -0.0289   0.1219   1.0000
   8.500   1.0999   0.02171   0.01360  -0.0288   0.1163   1.0000
   8.750   1.1252   0.02257   0.01453  -0.0285   0.1115   1.0000
   9.000   1.1501   0.02339   0.01536  -0.0283   0.1070   1.0000
   9.250   1.1733   0.02466   0.01652  -0.0280   0.1030   1.0000
   9.500   1.1979   0.02545   0.01747  -0.0277   0.0995   1.0000
   9.750   1.2218   0.02635   0.01840  -0.0274   0.0961   1.0000
  10.000   1.2445   0.02765   0.01959  -0.0270   0.0929   1.0000
  10.250   1.2671   0.02874   0.02084  -0.0265   0.0902   1.0000
  10.500   1.2893   0.02974   0.02197  -0.0261   0.0874   1.0000
  10.750   1.3113   0.03077   0.02301  -0.0256   0.0847   1.0000
  11.000   1.3329   0.03253   0.02467  -0.0252   0.0822   1.0000
  11.250   1.3519   0.03362   0.02603  -0.0245   0.0802   1.0000
  11.500   1.3705   0.03485   0.02742  -0.0238   0.0779   1.0000
  11.750   1.3894   0.03603   0.02865  -0.0231   0.0758   1.0000
  12.000   1.4098   0.03748   0.03003  -0.0226   0.0739   1.0000
  12.250   1.4240   0.03941   0.03215  -0.0217   0.0722   1.0000
  12.500   1.4346   0.04103   0.03404  -0.0205   0.0705   1.0000
  12.750   1.4452   0.04264   0.03582  -0.0193   0.0688   1.0000
  13.000   1.4561   0.04414   0.03741  -0.0182   0.0673   1.0000
  13.250   1.4714   0.04564   0.03886  -0.0174   0.0659   1.0000
  13.500   1.4780   0.04816   0.04149  -0.0162   0.0646   1.0000
  13.750   1.4657   0.05059   0.04422  -0.0139   0.0639   1.0000
  14.000   1.4540   0.05368   0.04758  -0.0130   0.0630   1.0000
  14.250   1.4434   0.05719   0.05133  -0.0131   0.0622   1.0000
  14.500   1.4339   0.06095   0.05530  -0.0139   0.0613   1.0000
  14.750   1.4269   0.06468   0.05918  -0.0150   0.0605   1.0000
  15.000   1.4186   0.06875   0.06340  -0.0165   0.0598   1.0000
  15.250   1.4135   0.07256   0.06731  -0.0179   0.0590   1.0000
  15.500   1.4253   0.07441   0.06907  -0.0173   0.0579   1.0000
  15.750   1.4039   0.08078   0.07565  -0.0202   0.0575   1.0000
  16.000   1.3698   0.08917   0.08433  -0.0253   0.0574   1.0000
  16.250   1.3304   0.09907   0.09452  -0.0316   0.0574   1.0000
  16.500   1.2832   0.11130   0.10702  -0.0398   0.0576   1.0000
  16.750   0.7080   0.18958   0.18623  -0.0665   0.0824   1.0000
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