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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 100,000
Max Cl/Cd: 33.83 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w153-il-100000-n5.txt
Download as CSV file: xf-fx77w153-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2452   0.10582   0.10005  -0.0122   0.5333   0.0623
  -9.250  -0.2623   0.09685   0.09106  -0.0170   0.5338   0.0423
  -8.750  -0.3632   0.09022   0.08429  -0.0177   0.5419   0.0368
  -8.500  -0.3557   0.08750   0.08155  -0.0182   0.5358   0.0364
  -8.250  -0.3521   0.08378   0.07782  -0.0204   0.5311   0.0358
  -8.000  -0.3528   0.07893   0.07295  -0.0246   0.5276   0.0351
  -7.750  -0.3589   0.07376   0.06771  -0.0284   0.5251   0.0343
  -7.500  -0.3892   0.06020   0.05371  -0.0360   0.5265   0.0314
  -7.250  -0.3840   0.05659   0.04990  -0.0363   0.5225   0.0312
  -7.000  -0.3777   0.05277   0.04583  -0.0363   0.5184   0.0311
  -6.750  -0.3700   0.04892   0.04165  -0.0360   0.5146   0.0309
  -6.500  -0.3604   0.04517   0.03749  -0.0353   0.5112   0.0308
  -6.000  -0.3338   0.03849   0.02983  -0.0332   0.5045   0.0310
  -5.750  -0.3170   0.03558   0.02634  -0.0319   0.5010   0.0316
  -5.500  -0.2949   0.03447   0.02515  -0.0315   0.4972   0.0325
  -5.250  -0.2728   0.03319   0.02361  -0.0309   0.4939   0.0338
  -5.000  -0.2504   0.03150   0.02150  -0.0300   0.4911   0.0351
  -4.750  -0.2265   0.02967   0.01922  -0.0291   0.4875   0.0362
  -4.500  -0.2014   0.02817   0.01744  -0.0285   0.4841   0.0372
  -4.250  -0.1759   0.02718   0.01632  -0.0281   0.4810   0.0384
  -4.000  -0.1497   0.02619   0.01514  -0.0276   0.4784   0.0402
  -3.750  -0.1229   0.02519   0.01383  -0.0270   0.4762   0.0427
  -3.500  -0.0970   0.02457   0.01321  -0.0267   0.4740   0.0458
  -3.250  -0.0704   0.02401   0.01255  -0.0264   0.4715   0.0507
  -3.000  -0.0439   0.02366   0.01215  -0.0261   0.4691   0.0572
  -2.750  -0.0182   0.02313   0.01169  -0.0258   0.4669   0.0621
  -2.500   0.0079   0.02266   0.01113  -0.0253   0.4649   0.0656
  -2.250   0.0335   0.02228   0.01075  -0.0249   0.4630   0.0702
  -2.000   0.0594   0.02198   0.01035  -0.0243   0.4613   0.0750
  -1.750   0.0851   0.02168   0.00998  -0.0238   0.4597   0.0803
  -1.500   0.1112   0.02144   0.00967  -0.0233   0.4578   0.0895
  -1.250   0.1370   0.02112   0.00951  -0.0230   0.4550   0.1089
  -1.000   0.1624   0.02063   0.00939  -0.0227   0.4524   0.1852
  -0.750   0.1868   0.01972   0.00935  -0.0225   0.4500   0.4081
  -0.500   0.2767   0.01863   0.00979  -0.0330   0.4465   0.9162
  -0.250   0.3635   0.01903   0.00985  -0.0440   0.4436   0.9996
   0.000   0.3890   0.01921   0.00981  -0.0437   0.4421   1.0000
   0.250   0.4136   0.01945   0.00999  -0.0434   0.4401   1.0000
   0.500   0.4382   0.01973   0.01020  -0.0431   0.4382   1.0000
   0.750   0.4627   0.02001   0.01041  -0.0427   0.4363   1.0000
   1.000   0.4871   0.02030   0.01063  -0.0423   0.4344   1.0000
   1.250   0.5115   0.02060   0.01084  -0.0419   0.4326   1.0000
   1.500   0.5359   0.02090   0.01106  -0.0414   0.4309   1.0000
   1.750   0.5604   0.02119   0.01126  -0.0410   0.4293   1.0000
   2.000   0.5848   0.02149   0.01146  -0.0405   0.4278   1.0000
   2.250   0.6095   0.02177   0.01162  -0.0400   0.4263   1.0000
   2.500   0.6328   0.02221   0.01208  -0.0395   0.4237   1.0000
   2.750   0.6557   0.02266   0.01257  -0.0390   0.4205   1.0000
   3.000   0.6790   0.02306   0.01296  -0.0384   0.4176   1.0000
   3.250   0.7026   0.02340   0.01327  -0.0379   0.4152   1.0000
   3.500   0.7267   0.02370   0.01351  -0.0373   0.4131   1.0000
   3.750   0.7510   0.02398   0.01372  -0.0368   0.4112   1.0000
   4.000   0.7758   0.02426   0.01390  -0.0362   0.4095   1.0000
   4.250   0.7957   0.02500   0.01480  -0.0355   0.4061   1.0000
   4.500   0.8164   0.02564   0.01552  -0.0348   0.4028   1.0000
   4.750   0.8383   0.02613   0.01605  -0.0341   0.4000   1.0000
   5.000   0.8613   0.02652   0.01642  -0.0335   0.3977   1.0000
   5.250   0.8849   0.02687   0.01674  -0.0329   0.3958   1.0000
   5.500   0.9091   0.02719   0.01702  -0.0324   0.3941   1.0000
   5.750   0.9289   0.02792   0.01784  -0.0316   0.3916   1.0000
   6.000   0.9434   0.02907   0.01919  -0.0304   0.3877   1.0000
   6.250   0.9614   0.02987   0.02008  -0.0295   0.3846   1.0000
   6.500   0.9821   0.03040   0.02063  -0.0287   0.3821   1.0000
   6.750   1.0058   0.03064   0.02088  -0.0281   0.3799   1.0000
   7.000   1.0319   0.03067   0.02084  -0.0276   0.3780   1.0000
   7.250   1.0381   0.03221   0.02263  -0.0258   0.3726   1.0000
   7.500   1.0529   0.03301   0.02352  -0.0245   0.3683   1.0000
   7.750   1.0750   0.03324   0.02378  -0.0238   0.3656   1.0000
   8.000   1.1003   0.03328   0.02381  -0.0232   0.3636   1.0000
   8.250   1.1269   0.03331   0.02381  -0.0229   0.3621   1.0000
   8.500   1.1071   0.03673   0.02760  -0.0195   0.3550   1.0000
   8.750   1.1169   0.03788   0.02885  -0.0181   0.3516   1.0000
   9.000   1.1370   0.03826   0.02928  -0.0173   0.3493   1.0000
   9.250   1.1625   0.03829   0.02931  -0.0168   0.3477   1.0000
   9.500   1.1912   0.03814   0.02916  -0.0166   0.3463   1.0000
  10.000   1.0923   0.04958   0.04098  -0.0113   0.3309   1.0000
  11.500   0.9175   0.09081   0.08253  -0.0209   0.2761   1.0000
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