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WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-080 (fx77080-il)
Reynolds number: 200,000
Max Cl/Cd: 41.98 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77080-il-200000.txt
Download as CSV file: xf-fx77080-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5721   0.07729   0.07387  -0.0107   1.0000   0.0620
  -9.750  -0.8243   0.05667   0.05258  -0.0267   1.0000   0.0359
  -9.500  -0.8410   0.05144   0.04712  -0.0255   1.0000   0.0353
  -9.250  -0.8519   0.04649   0.04185  -0.0237   1.0000   0.0347
  -9.000  -0.8576   0.04172   0.03666  -0.0216   1.0000   0.0342
  -8.750  -0.8572   0.03746   0.03191  -0.0192   1.0000   0.0342
  -8.500  -0.8509   0.03382   0.02780  -0.0169   1.0000   0.0341
  -8.250  -0.8399   0.03086   0.02439  -0.0148   1.0000   0.0347
  -8.000  -0.8245   0.02883   0.02194  -0.0128   1.0000   0.0361
  -7.750  -0.8096   0.02625   0.01897  -0.0110   1.0000   0.0377
  -7.500  -0.7912   0.02422   0.01685  -0.0097   1.0000   0.0398
  -7.250  -0.7710   0.02281   0.01529  -0.0084   1.0000   0.0420
  -7.000  -0.7499   0.02151   0.01380  -0.0070   1.0000   0.0444
  -6.750  -0.7282   0.02058   0.01266  -0.0057   1.0000   0.0475
  -6.500  -0.7086   0.01883   0.01093  -0.0043   1.0000   0.0516
  -6.250  -0.6872   0.01791   0.00993  -0.0030   1.0000   0.0562
  -6.000  -0.6669   0.01678   0.00876  -0.0015   1.0000   0.0617
  -5.750  -0.6454   0.01610   0.00805  -0.0002   1.0000   0.0695
  -5.500  -0.6253   0.01521   0.00720   0.0013   1.0000   0.0797
  -5.250  -0.6041   0.01457   0.00659   0.0027   1.0000   0.0957
  -5.000  -0.5835   0.01391   0.00605   0.0041   1.0000   0.1182
  -4.750  -0.5620   0.01343   0.00563   0.0053   1.0000   0.1434
  -4.500  -0.5403   0.01302   0.00525   0.0065   1.0000   0.1652
  -4.250  -0.5185   0.01262   0.00489   0.0077   1.0000   0.1851
  -4.000  -0.4972   0.01221   0.00457   0.0090   1.0000   0.2057
  -3.750  -0.4757   0.01183   0.00427   0.0102   1.0000   0.2292
  -3.500  -0.4549   0.01140   0.00398   0.0115   1.0000   0.2594
  -3.250  -0.4349   0.01093   0.00373   0.0130   1.0000   0.3017
  -3.000  -0.4165   0.01038   0.00351   0.0148   1.0000   0.3658
  -2.750  -0.3994   0.00982   0.00335   0.0169   1.0000   0.4521
  -2.500  -0.3837   0.00928   0.00327   0.0194   1.0000   0.5503
  -2.250  -0.3681   0.00883   0.00325   0.0222   1.0000   0.6493
  -2.000  -0.3500   0.00850   0.00331   0.0248   1.0000   0.7422
  -1.750  -0.3244   0.00834   0.00342   0.0260   1.0000   0.8275
  -1.500  -0.2801   0.00838   0.00356   0.0234   1.0000   0.9000
  -1.250  -0.2206   0.00853   0.00368   0.0174   1.0000   0.9411
  -1.000  -0.1609   0.00869   0.00377   0.0112   1.0000   0.9640
  -0.750  -0.1051   0.00881   0.00384   0.0056   1.0000   0.9804
  -0.500  -0.0477   0.00886   0.00384  -0.0004   1.0000   0.9925
  -0.250  -0.0050   0.00886   0.00382  -0.0038   1.0000   1.0000
   0.000   0.0000   0.00883   0.00379   0.0000   1.0000   1.0000
   0.250   0.0051   0.00886   0.00382   0.0038   1.0000   1.0000
   0.500   0.0474   0.00886   0.00384   0.0005   0.9926   1.0000
   0.750   0.1056   0.00881   0.00383  -0.0057   0.9801   1.0000
   1.000   0.1623   0.00868   0.00376  -0.0114   0.9634   1.0000
   1.250   0.2216   0.00853   0.00368  -0.0175   0.9400   1.0000
   1.500   0.2801   0.00838   0.00356  -0.0233   0.9005   1.0000
   1.750   0.3244   0.00834   0.00342  -0.0260   0.8277   1.0000
   2.000   0.3500   0.00851   0.00331  -0.0247   0.7406   1.0000
   2.250   0.3680   0.00884   0.00325  -0.0221   0.6482   1.0000
   2.500   0.3837   0.00928   0.00326  -0.0194   0.5489   1.0000
   2.750   0.3995   0.00981   0.00335  -0.0168   0.4525   1.0000
   3.000   0.4164   0.01039   0.00351  -0.0147   0.3644   1.0000
   3.250   0.4349   0.01093   0.00373  -0.0130   0.3008   1.0000
   3.500   0.4549   0.01141   0.00398  -0.0115   0.2588   1.0000
   3.750   0.4756   0.01183   0.00427  -0.0102   0.2292   1.0000
   4.000   0.4971   0.01221   0.00458  -0.0089   0.2059   1.0000
   4.250   0.5185   0.01263   0.00489  -0.0077   0.1853   1.0000
   4.500   0.5402   0.01302   0.00525  -0.0065   0.1653   1.0000
   4.750   0.5619   0.01343   0.00563  -0.0053   0.1434   1.0000
   5.000   0.5835   0.01390   0.00605  -0.0041   0.1185   1.0000
   5.250   0.6040   0.01458   0.00660  -0.0027   0.0960   1.0000
   5.500   0.6252   0.01523   0.00722  -0.0013   0.0798   1.0000
   6.000   0.6669   0.01678   0.00876   0.0015   0.0618   1.0000
   6.250   0.6872   0.01789   0.00992   0.0030   0.0560   1.0000
   6.500   0.7086   0.01881   0.01090   0.0043   0.0514   1.0000
   6.750   0.7279   0.02063   0.01271   0.0057   0.0471   1.0000
   7.000   0.7499   0.02144   0.01375   0.0070   0.0441   1.0000
   7.250   0.7709   0.02280   0.01528   0.0084   0.0418   1.0000
   7.500   0.7912   0.02423   0.01686   0.0097   0.0398   1.0000
   7.750   0.8095   0.02630   0.01903   0.0110   0.0378   1.0000
   8.000   0.8242   0.02893   0.02208   0.0129   0.0360   1.0000
   8.250   0.8396   0.03099   0.02453   0.0148   0.0350   1.0000
   8.500   0.8508   0.03388   0.02787   0.0169   0.0342   1.0000
   8.750   0.8569   0.03753   0.03198   0.0192   0.0341   1.0000
   9.000   0.8573   0.04181   0.03673   0.0216   0.0343   1.0000
   9.250   0.8511   0.04668   0.04202   0.0238   0.0348   1.0000
   9.500   0.8397   0.05168   0.04735   0.0255   0.0353   1.0000
   9.750   0.8262   0.05665   0.05250   0.0266   0.0361   1.0000
  10.000   0.8262   0.06030   0.05626   0.0276   0.0375   1.0000
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