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OAF139 AIRFOIL (oaf139-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: OAF139 AIRFOIL (oaf139-il)
Reynolds number: 100,000
Max Cl/Cd: 26.54 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf139-il-100000.txt
Download as CSV file: xf-oaf139-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF139 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.3086   0.08174   0.07583   0.0226   1.0000   0.1050
 -14.000  -1.3520   0.07338   0.06716   0.0187   1.0000   0.1048
 -13.750  -1.3892   0.06706   0.06051   0.0171   1.0000   0.1049
 -13.500  -1.4219   0.06240   0.05551   0.0181   1.0000   0.1053
 -13.250  -1.3810   0.06143   0.05486   0.0181   1.0000   0.1095
 -13.000  -1.3897   0.05840   0.05167   0.0192   1.0000   0.1115
 -12.750  -1.4033   0.05523   0.04822   0.0212   1.0000   0.1134
 -12.500  -1.4144   0.05189   0.04448   0.0231   1.0000   0.1155
 -12.250  -1.4158   0.04875   0.04098   0.0247   1.0000   0.1181
 -12.000  -1.3926   0.04735   0.03975   0.0250   1.0000   0.1220
 -11.750  -1.3828   0.04532   0.03751   0.0262   1.0000   0.1260
 -11.500  -1.3781   0.04287   0.03454   0.0277   1.0000   0.1297
 -11.250  -1.3535   0.04129   0.03321   0.0279   1.0000   0.1343
 -11.000  -1.3374   0.03969   0.03144   0.0288   1.0000   0.1394
 -10.750  -1.3219   0.03768   0.02914   0.0296   1.0000   0.1445
 -10.500  -1.2986   0.03656   0.02817   0.0300   1.0000   0.1502
 -10.250  -1.2821   0.03496   0.02617   0.0309   1.0000   0.1567
 -10.000  -1.2575   0.03373   0.02517   0.0312   1.0000   0.1631
  -9.750  -1.2381   0.03240   0.02352   0.0319   1.0000   0.1711
  -9.500  -1.2134   0.03129   0.02263   0.0322   1.0000   0.1787
  -9.250  -1.1916   0.03000   0.02116   0.0327   1.0000   0.1882
  -9.000  -1.1676   0.02905   0.02027   0.0331   1.0000   0.1983
  -8.750  -1.1436   0.02801   0.01928   0.0335   1.0000   0.2089
  -8.500  -1.1196   0.02701   0.01825   0.0338   1.0000   0.2214
  -8.250  -1.0952   0.02614   0.01732   0.0342   1.0000   0.2351
  -8.000  -1.0701   0.02546   0.01660   0.0345   1.0000   0.2496
  -7.750  -1.0441   0.02487   0.01614   0.0347   1.0000   0.2635
  -7.500  -1.0179   0.02434   0.01567   0.0350   1.0000   0.2778
  -7.250  -0.9914   0.02383   0.01522   0.0352   1.0000   0.2920
  -7.000  -0.9646   0.02335   0.01475   0.0354   1.0000   0.3062
  -6.750  -0.9374   0.02289   0.01427   0.0356   1.0000   0.3204
  -6.500  -0.9101   0.02246   0.01378   0.0356   1.0000   0.3348
  -6.250  -0.8822   0.02213   0.01351   0.0358   1.0000   0.3482
  -6.000  -0.8542   0.02179   0.01327   0.0360   1.0000   0.3606
  -5.750  -0.8260   0.02140   0.01290   0.0360   1.0000   0.3738
  -5.500  -0.7977   0.02102   0.01248   0.0360   1.0000   0.3878
  -5.250  -0.7691   0.02073   0.01222   0.0360   1.0000   0.4014
  -5.000  -0.7404   0.02043   0.01205   0.0362   1.0000   0.4136
  -4.750  -0.7116   0.02008   0.01174   0.0361   1.0000   0.4269
  -4.500  -0.6824   0.01973   0.01137   0.0360   1.0000   0.4411
  -4.250  -0.6532   0.01944   0.01117   0.0359   1.0000   0.4541
  -4.000  -0.6239   0.01911   0.01095   0.0359   1.0000   0.4660
  -3.750  -0.5940   0.01874   0.01062   0.0356   1.0000   0.4793
  -3.500  -0.5637   0.01841   0.01030   0.0351   1.0000   0.4933
  -3.250  -0.5336   0.01810   0.01017   0.0349   1.0000   0.5044
  -3.000  -0.5025   0.01774   0.00992   0.0343   1.0000   0.5173
  -2.750  -0.4697   0.01741   0.00964   0.0331   1.0000   0.5314
  -2.500  -0.4345   0.01710   0.00958   0.0313   1.0000   0.5436
  -2.250  -0.3991   0.01725   0.00976   0.0299   0.8915   0.5568
  -2.000  -0.3806   0.01749   0.00979   0.0326   0.8310   0.5694
  -1.750  -0.3587   0.01759   0.00983   0.0347   0.7899   0.5807
  -1.500  -0.3343   0.01760   0.00977   0.0361   0.7568   0.5931
  -1.250  -0.3084   0.01762   0.00965   0.0370   0.7284   0.6071
  -1.000  -0.2820   0.01762   0.00963   0.0379   0.7020   0.6204
  -0.750  -0.2553   0.01761   0.00960   0.0387   0.6780   0.6337
  -0.500  -0.2282   0.01760   0.00955   0.0394   0.6561   0.6486
  -0.250  -0.2009   0.01762   0.00951   0.0400   0.6359   0.6646
   0.000  -0.1733   0.01765   0.00951   0.0405   0.6169   0.6812
   0.250  -0.1463   0.01765   0.00955   0.0413   0.5988   0.6964
   0.500  -0.1190   0.01765   0.00958   0.0419   0.5811   0.7120
   0.750  -0.0915   0.01766   0.00963   0.0425   0.5639   0.7286
   1.000  -0.0643   0.01769   0.00969   0.0432   0.5474   0.7461
   1.250  -0.0375   0.01772   0.00976   0.0440   0.5313   0.7646
   1.500  -0.0116   0.01775   0.00981   0.0450   0.5156   0.7840
   1.750   0.0137   0.01778   0.00984   0.0462   0.5006   0.8048
   2.000   0.0386   0.01779   0.00987   0.0475   0.4849   0.8280
   2.250   0.0630   0.01777   0.00993   0.0489   0.4686   0.8525
   2.500   0.0863   0.01774   0.00997   0.0507   0.4528   0.8798
   2.750   0.1114   0.01769   0.00996   0.0521   0.4374   0.9107
   3.000   0.1453   0.01770   0.00997   0.0517   0.4206   0.9436
   3.250   0.1933   0.01787   0.01011   0.0480   0.4009   0.9722
   3.500   0.2488   0.01812   0.01031   0.0427   0.3801   0.9952
   3.750   0.2719   0.01815   0.01023   0.0421   0.3666   1.0000
   4.000   0.2976   0.01836   0.01022   0.0419   0.3536   1.0000
   4.250   0.3270   0.01863   0.01043   0.0412   0.3378   1.0000
   4.500   0.3570   0.01897   0.01075   0.0406   0.3222   1.0000
   4.750   0.3868   0.01936   0.01109   0.0401   0.3068   1.0000
   5.000   0.4165   0.01979   0.01147   0.0397   0.2920   1.0000
   5.250   0.4460   0.02024   0.01185   0.0393   0.2778   1.0000
   5.500   0.4750   0.02072   0.01217   0.0391   0.2648   1.0000
   5.750   0.5044   0.02120   0.01263   0.0387   0.2510   1.0000
   6.000   0.5340   0.02184   0.01334   0.0383   0.2374   1.0000
   6.250   0.5631   0.02256   0.01407   0.0379   0.2251   1.0000
   6.500   0.5915   0.02324   0.01459   0.0377   0.2145   1.0000
   6.750   0.6204   0.02393   0.01536   0.0373   0.2029   1.0000
   7.000   0.6489   0.02490   0.01644   0.0369   0.1920   1.0000
   7.250   0.6766   0.02574   0.01708   0.0368   0.1831   1.0000
   7.500   0.7048   0.02665   0.01823   0.0363   0.1727   1.0000
   7.750   0.7321   0.02780   0.01944   0.0360   0.1641   1.0000
   8.000   0.7594   0.02861   0.02022   0.0358   0.1558   1.0000
   8.250   0.7856   0.03014   0.02198   0.0353   0.1476   1.0000
   8.500   0.8123   0.03097   0.02269   0.0353   0.1408   1.0000
   8.750   0.8365   0.03297   0.02506   0.0346   0.1336   1.0000
   9.000   0.8622   0.03394   0.02594   0.0346   0.1277   1.0000
   9.250   0.8834   0.03650   0.02889   0.0339   0.1220   1.0000
   9.500   0.9063   0.03807   0.03058   0.0336   0.1167   1.0000
   9.750   0.9285   0.04003   0.03249   0.0335   0.1126   1.0000
  10.000   0.9375   0.04419   0.03737   0.0319   0.1085   1.0000
  10.250   0.9564   0.04607   0.03932   0.0318   0.1046   1.0000
  10.500   0.9800   0.04767   0.04069   0.0321   0.1015   1.0000
  10.750   0.9644   0.05440   0.04823   0.0291   0.1001   1.0000
  11.000   0.9278   0.06319   0.05752   0.0233   0.1001   1.0000
  11.250   0.8772   0.07447   0.06901   0.0136   0.1013   1.0000
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