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WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 50,000
Max Cl/Cd: 33.62 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx80080-il-50000.txt
Download as CSV file: xf-fx80080-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 80-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4679   0.10894   0.10211  -0.0249   1.0000   0.2099
  -8.500  -0.4532   0.10440   0.09757  -0.0233   1.0000   0.2228
  -8.250  -0.4448   0.10055   0.09376  -0.0223   1.0000   0.2351
  -8.000  -0.4412   0.09731   0.09059  -0.0214   1.0000   0.2473
  -7.750  -0.4401   0.09437   0.08774  -0.0205   1.0000   0.2603
  -7.500  -0.4407   0.09162   0.08508  -0.0193   1.0000   0.2750
  -7.250  -0.4456   0.08927   0.08284  -0.0177   1.0000   0.2912
  -7.000  -0.4565   0.08736   0.08109  -0.0157   1.0000   0.3070
  -6.750  -0.4429   0.08369   0.07745  -0.0131   1.0000   0.3299
  -6.500  -0.4588   0.08232   0.07625  -0.0104   1.0000   0.3494
  -6.250  -0.4559   0.07965   0.07366  -0.0068   1.0000   0.3773
  -6.000  -0.4407   0.07657   0.07060  -0.0023   1.0000   0.4173
  -5.750  -0.4149   0.07344   0.06740   0.0030   1.0000   0.4883
  -4.500  -0.4343   0.04917   0.04211  -0.0364   1.0000   0.2096
  -4.250  -0.3981   0.04295   0.03502  -0.0399   1.0000   0.1510
  -4.000  -0.3713   0.03915   0.03058  -0.0406   1.0000   0.1365
  -3.750  -0.3423   0.03590   0.02649  -0.0409   1.0000   0.1248
  -3.500  -0.3167   0.03296   0.02312  -0.0405   1.0000   0.1214
  -3.250  -0.2898   0.03056   0.02021  -0.0400   1.0000   0.1201
  -3.000  -0.2626   0.02885   0.01790  -0.0393   1.0000   0.1261
  -2.750  -0.2377   0.02699   0.01593  -0.0386   1.0000   0.1371
  -2.500  -0.2123   0.02534   0.01417  -0.0374   1.0000   0.1469
  -2.250  -0.1893   0.02402   0.01286  -0.0360   1.0000   0.1740
  -2.000  -0.1643   0.02253   0.01150  -0.0349   1.0000   0.2160
  -1.750  -0.1512   0.01830   0.01057  -0.0270   1.0000   1.0000
  -1.500  -0.1294   0.01839   0.00989  -0.0262   1.0000   1.0000
  -1.250  -0.1079   0.01851   0.00953  -0.0257   1.0000   1.0000
  -1.000  -0.0861   0.01867   0.00930  -0.0254   1.0000   1.0000
  -0.750  -0.0641   0.01887   0.00916  -0.0251   1.0000   1.0000
  -0.500  -0.0420   0.01909   0.00906  -0.0249   1.0000   1.0000
  -0.250  -0.0199   0.01935   0.00906  -0.0247   1.0000   1.0000
   0.000   0.0022   0.01963   0.00913  -0.0245   1.0000   1.0000
   0.250   0.0241   0.01995   0.00925  -0.0242   1.0000   1.0000
   0.500   0.0459   0.02029   0.00943  -0.0241   1.0000   1.0000
   0.750   0.0676   0.02066   0.00964  -0.0238   1.0000   1.0000
   1.000   0.0891   0.02106   0.00993  -0.0236   1.0000   1.0000
   1.250   0.1104   0.02149   0.01027  -0.0235   1.0000   1.0000
   1.500   0.1315   0.02195   0.01066  -0.0233   1.0000   1.0000
   1.750   0.1523   0.02245   0.01110  -0.0231   1.0000   1.0000
   2.000   0.1730   0.02298   0.01160  -0.0229   1.0000   1.0000
   2.250   0.1933   0.02355   0.01215  -0.0228   1.0000   1.0000
   2.500   0.2134   0.02416   0.01277  -0.0226   1.0000   1.0000
   2.750   0.2331   0.02482   0.01345  -0.0225   1.0000   1.0000
   3.000   0.2524   0.02552   0.01419  -0.0224   1.0000   1.0000
   3.250   0.2713   0.02628   0.01503  -0.0223   1.0000   1.0000
   3.500   0.2897   0.02709   0.01592  -0.0223   1.0000   1.0000
   3.750   0.3076   0.02798   0.01690  -0.0223   1.0000   1.0000
   4.000   0.3250   0.02894   0.01796  -0.0224   1.0000   1.0000
   4.250   0.3654   0.03056   0.01979  -0.0270   0.9889   1.0000
   4.500   0.4276   0.03238   0.02199  -0.0353   0.9608   1.0000
   4.750   0.4916   0.03379   0.02380  -0.0429   0.9278   1.0000
   5.000   0.5649   0.03446   0.02506  -0.0503   0.8862   1.0000
   5.250   0.6733   0.03228   0.02381  -0.0583   0.8236   1.0000
   5.500   0.7858   0.02445   0.01733  -0.0573   0.7211   1.0000
   5.750   0.7991   0.02377   0.01398  -0.0446   0.3080   1.0000
   6.000   0.8161   0.02700   0.01619  -0.0425   0.2139   1.0000
   6.250   0.8567   0.03011   0.01888  -0.0437   0.1618   1.0000
   6.500   0.8942   0.03315   0.02196  -0.0443   0.1363   1.0000
   6.750   0.9260   0.03660   0.02547  -0.0446   0.1202   1.0000
   7.000   0.9490   0.03944   0.02897  -0.0429   0.1114   1.0000
   7.250   0.9752   0.04363   0.03336  -0.0424   0.1073   1.0000
   7.500   0.9910   0.04749   0.03785  -0.0401   0.1053   1.0000
   7.750   0.9998   0.05100   0.04207  -0.0373   0.1026   1.0000
   8.000   1.0069   0.05504   0.04665  -0.0348   0.1013   1.0000
   8.250   1.0129   0.05978   0.05183  -0.0326   0.1038   1.0000
   8.500   1.0270   0.06571   0.05785  -0.0317   0.1066   1.0000
   8.750   1.0024   0.06979   0.06286  -0.0277   0.1148   1.0000
   9.000   0.9968   0.07517   0.06857  -0.0263   0.1230   1.0000
   9.250   0.9792   0.08096   0.07460  -0.0252   0.1314   1.0000
   9.500   0.9626   0.08745   0.08130  -0.0254   0.1486   1.0000
   9.750   0.9208   0.09187   0.08578  -0.0260   0.1505   1.0000
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