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WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il)
Reynolds number: 500,000
Max Cl/Cd: 106.84 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx08s176-il-500000-n5.txt
Download as CSV file: xf-fx08s176-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 08-S-176 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1096   0.09676   0.09234  -0.0873   0.5725   0.0080
 -11.250  -0.1128   0.09192   0.08753  -0.0893   0.5721   0.0081
 -11.000  -0.1225   0.08591   0.08156  -0.0918   0.5716   0.0082
 -10.750  -0.1239   0.08206   0.07774  -0.0938   0.5708   0.0085
 -10.500  -0.1287   0.07752   0.07323  -0.0961   0.5702   0.0086
 -10.250  -0.1306   0.07365   0.06940  -0.0983   0.5695   0.0087
 -10.000  -0.1544   0.06566   0.06149  -0.1035   0.5691   0.0087
  -9.750  -0.2233   0.05308   0.04889  -0.1102   0.5690   0.0086
  -9.500  -0.3010   0.04340   0.03896  -0.1047   0.5688   0.0087
  -9.250  -0.3714   0.02984   0.02454  -0.0969   0.5687   0.0092
  -9.000  -0.3588   0.02827   0.02277  -0.0954   0.5678   0.0096
  -8.750  -0.3491   0.02597   0.02013  -0.0935   0.5670   0.0101
  -8.500  -0.3353   0.02400   0.01781  -0.0920   0.5662   0.0108
  -8.250  -0.3177   0.02248   0.01599  -0.0908   0.5654   0.0114
  -8.000  -0.2964   0.02160   0.01490  -0.0901   0.5646   0.0119
  -7.750  -0.2753   0.02081   0.01400  -0.0894   0.5638   0.0124
  -7.500  -0.2518   0.02041   0.01353  -0.0890   0.5630   0.0128
  -7.250  -0.2279   0.02002   0.01305  -0.0887   0.5622   0.0133
  -7.000  -0.2043   0.01940   0.01229  -0.0883   0.5612   0.0138
  -6.750  -0.1800   0.01880   0.01157  -0.0879   0.5603   0.0145
  -6.500  -0.1552   0.01828   0.01093  -0.0876   0.5595   0.0153
  -6.250  -0.1299   0.01783   0.01037  -0.0873   0.5586   0.0160
  -6.000  -0.1041   0.01748   0.00992  -0.0871   0.5578   0.0164
  -5.750  -0.0807   0.01647   0.00881  -0.0866   0.5569   0.0172
  -5.500  -0.0556   0.01599   0.00829  -0.0864   0.5561   0.0179
  -5.250  -0.0300   0.01566   0.00794  -0.0862   0.5552   0.0187
  -5.000  -0.0042   0.01535   0.00759  -0.0860   0.5543   0.0195
  -4.750   0.0214   0.01499   0.00717  -0.0858   0.5534   0.0203
  -4.500   0.0468   0.01462   0.00675  -0.0856   0.5525   0.0208
  -4.250   0.0725   0.01430   0.00636  -0.0853   0.5516   0.0214
  -4.000   0.0982   0.01400   0.00601  -0.0851   0.5506   0.0219
  -3.750   0.1242   0.01374   0.00570  -0.0850   0.5497   0.0225
  -3.500   0.1492   0.01336   0.00528  -0.0847   0.5489   0.0239
  -3.250   0.1755   0.01313   0.00503  -0.0846   0.5481   0.0251
  -3.000   0.2021   0.01296   0.00482  -0.0846   0.5473   0.0261
  -2.750   0.2291   0.01284   0.00464  -0.0847   0.5465   0.0274
  -2.500   0.2561   0.01271   0.00449  -0.0847   0.5457   0.0288
  -2.250   0.2832   0.01258   0.00436  -0.0848   0.5449   0.0309
  -2.000   0.3102   0.01244   0.00426  -0.0849   0.5440   0.0369
  -1.750   0.3372   0.01229   0.00420  -0.0850   0.5428   0.0556
  -1.500   0.3646   0.01219   0.00414  -0.0852   0.5417   0.0697
  -1.250   0.3922   0.01212   0.00408  -0.0854   0.5407   0.0809
  -1.000   0.4193   0.01195   0.00402  -0.0856   0.5398   0.1151
  -0.750   0.4453   0.01156   0.00397  -0.0858   0.5388   0.2263
  -0.500   0.4675   0.01006   0.00382  -0.0863   0.5378   0.6483
  -0.250   0.4884   0.00991   0.00419  -0.0845   0.5367   0.7880
   0.000   0.5146   0.01010   0.00437  -0.0841   0.5354   0.8212
   0.250   0.5414   0.01028   0.00451  -0.0838   0.5342   0.8377
   0.500   0.5695   0.01042   0.00458  -0.0839   0.5329   0.8475
   0.750   0.5958   0.01053   0.00467  -0.0837   0.5315   0.8517
   1.000   0.6233   0.01059   0.00474  -0.0838   0.5297   0.8553
   1.250   0.6519   0.01065   0.00477  -0.0842   0.5278   0.8602
   1.500   0.6786   0.01070   0.00482  -0.0841   0.5258   0.8633
   1.750   0.7046   0.01075   0.00487  -0.0839   0.5239   0.8665
   2.000   0.7312   0.01083   0.00493  -0.0838   0.5223   0.8710
   2.250   0.7600   0.01088   0.00495  -0.0843   0.5211   0.8741
   2.500   0.7895   0.01093   0.00497  -0.0850   0.5199   0.8762
   2.750   0.8167   0.01098   0.00500  -0.0851   0.5188   0.8775
   3.000   0.8438   0.01105   0.00507  -0.0853   0.5176   0.8789
   3.250   0.8708   0.01111   0.00517  -0.0855   0.5160   0.8804
   3.500   0.8980   0.01118   0.00527  -0.0857   0.5143   0.8819
   3.750   0.9255   0.01124   0.00535  -0.0860   0.5124   0.8835
   4.000   0.9532   0.01129   0.00542  -0.0864   0.5105   0.8853
   4.250   0.9812   0.01133   0.00548  -0.0868   0.5086   0.8870
   4.500   1.0096   0.01137   0.00552  -0.0873   0.5070   0.8884
   4.750   1.0383   0.01143   0.00557  -0.0880   0.5054   0.8898
   5.000   1.0660   0.01150   0.00567  -0.0884   0.5037   0.8911
   5.250   1.0918   0.01158   0.00582  -0.0884   0.5016   0.8924
   5.500   1.1178   0.01165   0.00596  -0.0885   0.4993   0.8936
   5.750   1.1440   0.01172   0.00609  -0.0886   0.4969   0.8950
   6.000   1.1704   0.01178   0.00618  -0.0887   0.4946   0.8963
   6.250   1.1966   0.01180   0.00620  -0.0888   0.4914   0.8977
   6.500   1.2219   0.01185   0.00632  -0.0888   0.4847   0.8992
   6.750   1.2467   0.01186   0.00632  -0.0887   0.4764   0.9005
   7.000   1.2709   0.01194   0.00643  -0.0886   0.4656   0.9016
   7.250   1.2927   0.01210   0.00655  -0.0880   0.4505   0.9028
   7.500   1.3085   0.01247   0.00681  -0.0865   0.4246   0.9042
   7.750   1.3129   0.01319   0.00737  -0.0830   0.3941   0.9061
   8.000   1.3107   0.01394   0.00803  -0.0783   0.3704   0.9083
   8.250   1.3045   0.01492   0.00895  -0.0733   0.3512   0.9109
   8.500   1.2980   0.01608   0.01008  -0.0688   0.3348   0.9136
   8.750   1.2893   0.01761   0.01159  -0.0649   0.3215   0.9169
   9.000   1.2667   0.02048   0.01445  -0.0608   0.3016   0.9202
   9.250   1.2545   0.02321   0.01720  -0.0583   0.2879   0.9229
   9.500   1.2288   0.02707   0.02101  -0.0552   0.2637   0.9262
   9.750   1.2020   0.03100   0.02484  -0.0520   0.2368   0.9298
  10.250   1.1506   0.03874   0.03236  -0.0463   0.1818   0.9352
  10.500   1.1233   0.04306   0.03648  -0.0437   0.1415   0.9379
  10.750   1.0986   0.04752   0.04071  -0.0418   0.0951   0.9405
  11.000   1.0781   0.05190   0.04487  -0.0403   0.0479   0.9428
  11.250   1.0665   0.05569   0.04852  -0.0395   0.0131   0.9451
  11.750   1.0803   0.05977   0.05270  -0.0392   0.0081   0.9502
  12.000   1.0885   0.06177   0.05477  -0.0392   0.0074   0.9537
  12.250   1.0969   0.06382   0.05689  -0.0394   0.0070   0.9581
  12.500   1.1034   0.06624   0.05941  -0.0397   0.0063   0.9645
  12.750   1.1115   0.06857   0.06184  -0.0402   0.0060   0.9752
  13.250   1.1247   0.07323   0.06664  -0.0408   0.0057   1.0000
  13.500   1.1317   0.07562   0.06909  -0.0411   0.0056   1.0000
  13.750   1.1375   0.07817   0.07172  -0.0415   0.0053   1.0000
  14.000   1.1425   0.08087   0.07449  -0.0419   0.0051   1.0000
  14.250   1.1485   0.08345   0.07713  -0.0424   0.0048   1.0000
  14.500   1.1522   0.08639   0.08015  -0.0430   0.0046   1.0000
  14.750   1.1559   0.08935   0.08318  -0.0435   0.0044   1.0000
  15.000   1.1588   0.09243   0.08634  -0.0442   0.0043   1.0000
  15.250   1.1613   0.09560   0.08958  -0.0448   0.0042   1.0000
  15.500   1.1623   0.09904   0.09309  -0.0456   0.0041   1.0000
  15.750   1.1637   0.10244   0.09656  -0.0464   0.0040   1.0000
  16.000   1.1620   0.10633   0.10052  -0.0474   0.0039   1.0000
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