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GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 648 AIRFOIL (goe648-il)
Reynolds number: 100,000
Max Cl/Cd: 44.15 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe648-il-100000-n5.txt
Download as CSV file: xf-goe648-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 648 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6800   0.05337   0.04759  -0.0645   1.0000   0.0490
 -10.250  -0.6911   0.05199   0.04620  -0.0611   1.0000   0.0494
 -10.000  -0.6759   0.05017   0.04430  -0.0623   0.9955   0.0503
  -9.750  -0.6600   0.04711   0.04099  -0.0648   0.9880   0.0516
  -9.500  -0.6476   0.04316   0.03657  -0.0672   0.9805   0.0531
  -9.250  -0.6386   0.03914   0.03184  -0.0682   0.9717   0.0551
  -9.000  -0.6102   0.03821   0.03094  -0.0694   0.9664   0.0565
  -8.750  -0.5867   0.03675   0.02931  -0.0699   0.9594   0.0582
  -8.500  -0.5599   0.03467   0.02686  -0.0713   0.9546   0.0604
  -8.250  -0.5411   0.03300   0.02484  -0.0707   0.9460   0.0624
  -8.000  -0.5094   0.03204   0.02386  -0.0721   0.9414   0.0645
  -7.750  -0.4860   0.03088   0.02253  -0.0718   0.9340   0.0666
  -7.500  -0.4585   0.02951   0.02081  -0.0722   0.9279   0.0694
  -7.250  -0.4241   0.02849   0.01979  -0.0739   0.9241   0.0720
  -7.000  -0.4029   0.02771   0.01894  -0.0729   0.9153   0.0746
  -6.750  -0.3708   0.02665   0.01763  -0.0737   0.9103   0.0780
  -6.500  -0.3348   0.02569   0.01669  -0.0755   0.9069   0.0816
  -6.250  -0.3146   0.02507   0.01604  -0.0741   0.8971   0.0851
  -6.000  -0.2803   0.02419   0.01501  -0.0752   0.8926   0.0896
  -5.750  -0.2493   0.02348   0.01436  -0.0759   0.8870   0.0941
  -5.500  -0.2230   0.02290   0.01369  -0.0755   0.8788   0.0993
  -5.250  -0.1871   0.02216   0.01300  -0.0770   0.8742   0.1053
  -5.000  -0.1608   0.02167   0.01244  -0.0765   0.8653   0.1117
  -4.750  -0.1278   0.02101   0.01184  -0.0773   0.8579   0.1190
  -4.500  -0.0975   0.02046   0.01125  -0.0774   0.8488   0.1276
  -4.250  -0.0654   0.01987   0.01068  -0.0779   0.8395   0.1377
  -4.000  -0.0375   0.01935   0.01020  -0.0775   0.8285   0.1488
  -3.750  -0.0037   0.01875   0.00963  -0.0783   0.8193   0.1641
  -3.500   0.0209   0.01831   0.00925  -0.0774   0.8062   0.1825
  -3.250   0.0506   0.01780   0.00881  -0.0773   0.7946   0.2099
  -3.000   0.0795   0.01734   0.00844  -0.0772   0.7823   0.2463
  -2.750   0.1031   0.01701   0.00822  -0.0761   0.7688   0.2837
  -2.500   0.1299   0.01665   0.00797  -0.0756   0.7572   0.3260
  -2.250   0.1572   0.01629   0.00775  -0.0752   0.7452   0.3736
  -2.000   0.1800   0.01604   0.00766  -0.0739   0.7312   0.4241
  -1.750   0.2048   0.01581   0.00758  -0.0729   0.7179   0.4799
  -1.500   0.2311   0.01561   0.00747  -0.0720   0.7048   0.5342
  -1.250   0.2567   0.01542   0.00738  -0.0710   0.6909   0.5912
  -1.000   0.2807   0.01528   0.00737  -0.0696   0.6755   0.6460
  -0.750   0.3053   0.01518   0.00735  -0.0682   0.6601   0.6964
  -0.500   0.3305   0.01512   0.00731  -0.0669   0.6444   0.7411
  -0.250   0.3566   0.01509   0.00726  -0.0659   0.6286   0.7824
   0.000   0.3853   0.01508   0.00722  -0.0653   0.6120   0.8226
   0.250   0.4202   0.01512   0.00720  -0.0661   0.5935   0.8625
   0.500   0.4644   0.01524   0.00721  -0.0688   0.5724   0.8993
   0.750   0.5128   0.01541   0.00721  -0.0726   0.5498   0.9317
   1.000   0.5586   0.01562   0.00722  -0.0761   0.5276   0.9619
   1.250   0.6029   0.01586   0.00728  -0.0795   0.5041   0.9919
   1.500   0.6249   0.01610   0.00732  -0.0786   0.4845   1.0000
   1.750   0.6406   0.01632   0.00736  -0.0764   0.4668   1.0000
   2.000   0.6575   0.01657   0.00744  -0.0744   0.4505   1.0000
   2.250   0.6750   0.01685   0.00754  -0.0724   0.4359   1.0000
   2.500   0.6933   0.01713   0.00768  -0.0706   0.4223   1.0000
   2.750   0.7123   0.01743   0.00784  -0.0690   0.4103   1.0000
   3.000   0.7317   0.01776   0.00801  -0.0674   0.4001   1.0000
   3.250   0.7517   0.01808   0.00823  -0.0659   0.3903   1.0000
   3.500   0.7722   0.01843   0.00844  -0.0646   0.3823   1.0000
   3.750   0.7930   0.01877   0.00871  -0.0633   0.3740   1.0000
   4.000   0.8140   0.01916   0.00895  -0.0621   0.3672   1.0000
   4.250   0.8354   0.01951   0.00927  -0.0609   0.3599   1.0000
   4.500   0.8569   0.01990   0.00957  -0.0598   0.3535   1.0000
   4.750   0.8791   0.02032   0.00987  -0.0589   0.3478   1.0000
   5.000   0.9005   0.02070   0.01026  -0.0578   0.3416   1.0000
   5.250   0.9223   0.02111   0.01062  -0.0568   0.3360   1.0000
   5.750   0.9665   0.02199   0.01142  -0.0549   0.3257   1.0000
   6.000   0.9879   0.02242   0.01186  -0.0539   0.3204   1.0000
   6.250   1.0101   0.02289   0.01226  -0.0531   0.3157   1.0000
   6.500   1.0327   0.02339   0.01271  -0.0523   0.3111   1.0000
   6.750   1.0525   0.02385   0.01325  -0.0511   0.3062   1.0000
   7.000   1.0732   0.02433   0.01374  -0.0500   0.3015   1.0000
   7.250   1.0949   0.02483   0.01420  -0.0491   0.2972   1.0000
   7.500   1.1166   0.02537   0.01473  -0.0483   0.2930   1.0000
   7.750   1.1337   0.02589   0.01535  -0.0467   0.2882   1.0000
   8.000   1.1524   0.02641   0.01591  -0.0454   0.2837   1.0000
   8.250   1.1728   0.02694   0.01644  -0.0444   0.2798   1.0000
   8.500   1.1941   0.02752   0.01699  -0.0436   0.2761   1.0000
   8.750   1.2069   0.02810   0.01773  -0.0413   0.2717   1.0000
   9.000   1.2216   0.02868   0.01839  -0.0395   0.2674   1.0000
   9.250   1.2382   0.02924   0.01897  -0.0379   0.2636   1.0000
   9.500   1.2585   0.02981   0.01949  -0.0370   0.2602   1.0000
   9.750   1.2695   0.03055   0.02038  -0.0348   0.2564   1.0000
  10.000   1.2811   0.03129   0.02127  -0.0327   0.2524   1.0000
  10.250   1.2946   0.03198   0.02203  -0.0309   0.2488   1.0000
  10.500   1.3103   0.03261   0.02266  -0.0295   0.2454   1.0000
  10.750   1.3261   0.03332   0.02339  -0.0282   0.2423   1.0000
  11.000   1.3311   0.03434   0.02462  -0.0256   0.2385   1.0000
  11.250   1.3392   0.03528   0.02568  -0.0235   0.2347   1.0000
  11.500   1.3502   0.03610   0.02656  -0.0218   0.2313   1.0000
  11.750   1.3648   0.03681   0.02728  -0.0206   0.2284   1.0000
  12.000   1.3693   0.03799   0.02860  -0.0185   0.2249   1.0000
  12.250   1.3694   0.03939   0.03019  -0.0161   0.2209   1.0000
  12.500   1.3737   0.04058   0.03146  -0.0143   0.2171   1.0000
  12.750   1.3828   0.04146   0.03235  -0.0129   0.2135   1.0000
  13.000   1.3850   0.04294   0.03394  -0.0113   0.2101   1.0000
  13.250   1.3798   0.04505   0.03627  -0.0095   0.2063   1.0000
  13.500   1.3794   0.04689   0.03822  -0.0082   0.2028   1.0000
  13.750   1.3844   0.04829   0.03966  -0.0072   0.1994   1.0000
  14.000   1.3875   0.04996   0.04137  -0.0062   0.1962   1.0000
  14.250   1.3721   0.05344   0.04511  -0.0053   0.1925   1.0000
  14.500   1.3629   0.05652   0.04834  -0.0048   0.1888   1.0000
  14.750   1.3625   0.05881   0.05070  -0.0045   0.1855   1.0000
  15.000   1.3699   0.06036   0.05224  -0.0042   0.1825   1.0000
  15.250   1.3370   0.06678   0.05897  -0.0051   0.1793   1.0000
  15.500   1.3043   0.07379   0.06621  -0.0069   0.1759   1.0000
  15.750   1.2880   0.07894   0.07148  -0.0083   0.1726   1.0000
  16.000   1.3055   0.07932   0.07183  -0.0079   0.1697   1.0000
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