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WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il)
Reynolds number: 500,000
Max Cl/Cd: 108.76 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx08s176-il-500000.txt
Download as CSV file: xf-fx08s176-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0150   0.09123   0.08724  -0.0847   0.5975   0.0199
 -10.750  -0.0091   0.08840   0.08442  -0.0855   0.5968   0.0207
 -10.500  -0.0066   0.08491   0.08095  -0.0868   0.5962   0.0211
 -10.250  -0.0057   0.08116   0.07722  -0.0883   0.5955   0.0224
 -10.000  -0.0060   0.07717   0.07326  -0.0899   0.5949   0.0228
  -9.750  -0.0118   0.07219   0.06830  -0.0925   0.5944   0.0238
  -9.500  -0.0204   0.06648   0.06263  -0.0964   0.5939   0.0244
  -9.250  -0.0271   0.06113   0.05730  -0.0997   0.5933   0.0245
  -9.000  -0.0425   0.05441   0.05059  -0.1052   0.5929   0.0245
  -8.750  -0.0593   0.04972   0.04585  -0.1074   0.5923   0.0245
  -8.500  -0.0774   0.04588   0.04196  -0.1074   0.5916   0.0245
  -8.250  -0.0943   0.04296   0.03897  -0.1055   0.5909   0.0245
  -8.000  -0.1113   0.03980   0.03569  -0.1027   0.5901   0.0245
  -7.500  -0.1568   0.04300   0.03828  -0.1023   0.5898   0.0253
  -7.250  -0.1458   0.04125   0.03648  -0.1013   0.5889   0.0257
  -7.000  -0.1333   0.03974   0.03488  -0.1003   0.5879   0.0263
  -6.750  -0.1180   0.03865   0.03371  -0.0996   0.5869   0.0275
  -6.500  -0.1040   0.03662   0.03145  -0.0981   0.5861   0.0300
  -6.250  -0.1122   0.02741   0.02134  -0.0924   0.5856   0.0231
  -6.000  -0.0962   0.02448   0.01798  -0.0906   0.5846   0.0230
  -5.750  -0.0751   0.02258   0.01576  -0.0896   0.5838   0.0235
  -5.500  -0.0503   0.02229   0.01527  -0.0890   0.5830   0.0247
  -5.250  -0.0279   0.01970   0.01244  -0.0883   0.5822   0.0256
  -5.000  -0.0026   0.01879   0.01148  -0.0881   0.5812   0.0265
  -4.750   0.0231   0.01815   0.01077  -0.0879   0.5801   0.0274
  -4.500   0.0491   0.01762   0.01020  -0.0876   0.5789   0.0286
  -4.250   0.0752   0.01720   0.00973  -0.0874   0.5776   0.0300
  -4.000   0.1010   0.01669   0.00915  -0.0871   0.5765   0.0309
  -3.750   0.1269   0.01630   0.00870  -0.0869   0.5755   0.0316
  -3.500   0.1505   0.01560   0.00796  -0.0863   0.5745   0.0328
  -3.250   0.1751   0.01518   0.00753  -0.0859   0.5736   0.0349
  -3.000   0.2011   0.01496   0.00729  -0.0858   0.5727   0.0371
  -2.750   0.2273   0.01477   0.00705  -0.0857   0.5718   0.0393
  -2.500   0.2536   0.01459   0.00681  -0.0856   0.5709   0.0418
  -2.250   0.2798   0.01449   0.00672  -0.0855   0.5697   0.0484
  -2.000   0.3059   0.01437   0.00665  -0.0854   0.5687   0.0650
  -1.750   0.3315   0.01413   0.00652  -0.0853   0.5677   0.0935
  -1.500   0.3563   0.01376   0.00648  -0.0853   0.5666   0.1779
  -1.250   0.3738   0.01200   0.00634  -0.0850   0.5654   0.6520
  -1.000   0.3925   0.01201   0.00688  -0.0826   0.5642   0.7979
  -0.750   0.4188   0.01233   0.00717  -0.0821   0.5628   0.8315
  -0.500   0.4420   0.01270   0.00752  -0.0807   0.5616   0.8484
  -0.250   0.4641   0.01306   0.00786  -0.0791   0.5603   0.8625
   0.000   0.4850   0.01332   0.00810  -0.0771   0.5591   0.8723
   0.250   0.5077   0.01344   0.00818  -0.0757   0.5577   0.8797
   0.500   0.5313   0.01359   0.00826  -0.0746   0.5564   0.8877
   0.750   0.5548   0.01379   0.00839  -0.0735   0.5548   0.8936
   1.000   0.5759   0.01380   0.00843  -0.0721   0.5530   0.8992
   1.250   0.6009   0.01384   0.00846  -0.0717   0.5511   0.9055
   1.500   0.6237   0.01382   0.00844  -0.0707   0.5493   0.9083
   1.750   0.6473   0.01386   0.00848  -0.0700   0.5479   0.9121
   2.000   0.6728   0.01393   0.00853  -0.0697   0.5465   0.9181
   2.250   0.6951   0.01387   0.00846  -0.0686   0.5452   0.9220
   2.500   0.7216   0.01382   0.00838  -0.0686   0.5439   0.9241
   2.750   0.7495   0.01379   0.00831  -0.0689   0.5428   0.9262
   3.000   0.7783   0.01379   0.00826  -0.0694   0.5415   0.9281
   3.250   0.8073   0.01394   0.00836  -0.0702   0.5402   0.9300
   3.500   0.8332   0.01399   0.00847  -0.0703   0.5386   0.9326
   3.750   0.8540   0.01396   0.00850  -0.0692   0.5368   0.9353
   4.000   0.8775   0.01396   0.00854  -0.0687   0.5349   0.9377
   4.250   0.9032   0.01396   0.00855  -0.0686   0.5332   0.9398
   4.500   0.9298   0.01393   0.00855  -0.0688   0.5315   0.9419
   4.750   0.9578   0.01390   0.00851  -0.0692   0.5301   0.9438
   5.000   0.9872   0.01386   0.00846  -0.0700   0.5287   0.9454
   5.250   1.0175   0.01385   0.00843  -0.0710   0.5274   0.9466
   5.500   1.0440   0.01386   0.00843  -0.0710   0.5258   0.9484
   5.750   1.0625   0.01385   0.00854  -0.0696   0.5234   0.9514
   6.000   1.0855   0.01385   0.00861  -0.0692   0.5209   0.9536
   6.250   1.1112   0.01381   0.00863  -0.0692   0.5186   0.9554
   6.500   1.1390   0.01375   0.00859  -0.0697   0.5166   0.9567
   6.750   1.1684   0.01369   0.00853  -0.0705   0.5148   0.9578
   7.000   1.1997   0.01350   0.00831  -0.0715   0.5123   0.9588
   7.250   1.2192   0.01338   0.00833  -0.0705   0.5076   0.9608
   7.500   1.2440   0.01295   0.00791  -0.0702   0.5018   0.9623
   7.750   1.2703   0.01271   0.00766  -0.0702   0.4973   0.9637
   8.000   1.2902   0.01265   0.00773  -0.0693   0.4912   0.9657
   8.250   1.3135   0.01242   0.00748  -0.0688   0.4837   0.9676
   8.500   1.3311   0.01235   0.00747  -0.0674   0.4722   0.9706
   8.750   1.3465   0.01238   0.00750  -0.0657   0.4572   0.9733
   9.000   1.3568   0.01262   0.00772  -0.0632   0.4363   0.9773
   9.250   1.3605   0.01330   0.00830  -0.0601   0.4096   0.9831
   9.500   1.3575   0.01483   0.00968  -0.0575   0.3759   1.0000
   9.750   1.3419   0.01721   0.01196  -0.0542   0.3506   1.0000
  10.000   1.3323   0.02007   0.01481  -0.0529   0.3337   1.0000
  10.250   1.3175   0.02371   0.01841  -0.0518   0.3160   1.0000
  10.500   1.3028   0.02728   0.02195  -0.0505   0.2981   1.0000
  10.750   1.2800   0.03136   0.02594  -0.0486   0.2724   1.0000
  11.000   1.2647   0.03479   0.02930  -0.0470   0.2498   1.0000
  11.250   1.2269   0.04009   0.03437  -0.0444   0.2109   1.0000
  11.500   1.1980   0.04504   0.03910  -0.0426   0.1726   1.0000
  11.750   1.1716   0.05000   0.04381  -0.0411   0.1275   1.0000
  12.000   1.1527   0.05449   0.04808  -0.0402   0.0871   1.0000
  12.250   1.1292   0.05967   0.05301  -0.0393   0.0415   1.0000
  12.500   1.1233   0.06325   0.05650  -0.0392   0.0183   1.0000
  12.750   1.1247   0.06612   0.05936  -0.0392   0.0130   1.0000
  13.000   1.1296   0.06866   0.06197  -0.0394   0.0119   1.0000
  13.250   1.1346   0.07122   0.06461  -0.0396   0.0109   1.0000
  13.500   1.1410   0.07367   0.06713  -0.0399   0.0105   1.0000
  13.750   1.1451   0.07643   0.06998  -0.0402   0.0100   1.0000
  14.000   1.1504   0.07904   0.07266  -0.0406   0.0097   1.0000
  14.250   1.1533   0.08201   0.07571  -0.0410   0.0094   1.0000
  14.500   1.1559   0.08505   0.07883  -0.0414   0.0092   1.0000
  14.750   1.1581   0.08820   0.08206  -0.0420   0.0090   1.0000
  15.000   1.1580   0.09170   0.08563  -0.0426   0.0088   1.0000
  15.250   1.1572   0.09532   0.08934  -0.0433   0.0086   1.0000
  15.500   1.1559   0.09905   0.09316  -0.0440   0.0084   1.0000
  15.750   1.1568   0.10254   0.09672  -0.0448   0.0084   1.0000
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