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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 100,000
Max Cl/Cd: 66.63 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe427-il-100000.txt
Download as CSV file: xf-goe427-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3510   0.10980   0.10489  -0.0262   1.0000   0.0434
  -8.250  -0.3573   0.10907   0.10426  -0.0258   1.0000   0.0436
  -8.000  -0.3594   0.10797   0.10325  -0.0269   1.0000   0.0437
  -7.750  -0.3578   0.10648   0.10182  -0.0288   1.0000   0.0439
  -7.500  -0.3535   0.10462   0.10000  -0.0308   1.0000   0.0440
  -7.250  -0.3522   0.09805   0.09348  -0.0270   1.0000   0.0447
  -7.000  -0.3473   0.09260   0.08805  -0.0222   1.0000   0.0462
  -6.750  -0.3451   0.08989   0.08538  -0.0212   1.0000   0.0472
  -6.500  -0.3430   0.08746   0.08300  -0.0207   1.0000   0.0483
  -6.250  -0.3404   0.08503   0.08062  -0.0206   1.0000   0.0497
  -6.000  -0.3366   0.08264   0.07827  -0.0210   1.0000   0.0513
  -5.750  -0.3306   0.08029   0.07595  -0.0222   1.0000   0.0540
  -5.500  -0.3115   0.07902   0.07464  -0.0291   1.0000   0.0569
  -5.250  -0.2833   0.07748   0.07298  -0.0377   1.0000   0.0578
  -5.000  -0.2966   0.07202   0.06769  -0.0299   1.0000   0.0595
  -4.750  -0.2914   0.06911   0.06481  -0.0282   1.0000   0.0618
  -4.500  -0.2786   0.06639   0.06208  -0.0293   1.0000   0.0650
  -4.250  -0.2247   0.06494   0.06028  -0.0426   1.0000   0.0713
  -4.000  -0.2282   0.06026   0.05572  -0.0385   1.0000   0.0726
  -3.750  -0.2197   0.05738   0.05287  -0.0371   1.0000   0.0759
  -3.500  -0.1727   0.05524   0.05038  -0.0458   1.0000   0.0848
  -3.250  -0.1681   0.05156   0.04684  -0.0434   1.0000   0.0872
  -3.000  -0.1275   0.04983   0.04476  -0.0491   1.0000   0.0984
  -2.750  -0.1213   0.04635   0.04144  -0.0469   1.0000   0.1027
  -2.500  -0.0941   0.04394   0.03889  -0.0492   1.0000   0.1154
  -2.250  -0.0664   0.04162   0.03639  -0.0513   1.0000   0.1285
  -2.000  -0.0211   0.03886   0.03346  -0.0565   0.9946   0.1474
  -1.750   0.0238   0.03624   0.03064  -0.0613   0.9881   0.1720
  -1.000   0.1843   0.02712   0.01969  -0.0753   0.9717   0.1083
  -0.750   0.2276   0.02510   0.01718  -0.0779   0.9644   0.1049
  -0.500   0.2752   0.02334   0.01475  -0.0808   0.9578   0.0998
  -0.250   0.3152   0.02252   0.01377  -0.0832   0.9479   0.1092
   0.000   0.3608   0.02148   0.01250  -0.0862   0.9400   0.1128
   0.250   0.4048   0.02062   0.01163  -0.0891   0.9302   0.1227
   0.500   0.4452   0.01984   0.01097  -0.0912   0.9189   0.1465
   0.750   0.5056   0.01711   0.01003  -0.0971   0.9150   1.0000
   1.000   0.5471   0.01696   0.00963  -0.0993   0.9024   1.0000
   1.250   0.5885   0.01675   0.00930  -0.1015   0.8901   1.0000
   1.500   0.6301   0.01649   0.00897  -0.1037   0.8780   1.0000
   1.750   0.6702   0.01619   0.00865  -0.1054   0.8655   1.0000
   2.000   0.7090   0.01587   0.00832  -0.1068   0.8525   1.0000
   2.250   0.7462   0.01557   0.00803  -0.1079   0.8384   1.0000
   2.500   0.7817   0.01532   0.00779  -0.1085   0.8232   1.0000
   2.750   0.8165   0.01503   0.00757  -0.1089   0.8064   1.0000
   3.000   0.8460   0.01475   0.00727  -0.1080   0.7823   1.0000
   3.250   0.8738   0.01451   0.00698  -0.1066   0.7547   1.0000
   3.500   0.9016   0.01454   0.00700  -0.1059   0.7328   1.0000
   3.750   0.9267   0.01471   0.00726  -0.1048   0.7102   1.0000
   4.000   0.9511   0.01486   0.00742  -0.1035   0.6854   1.0000
   4.250   0.9738   0.01494   0.00748  -0.1017   0.6546   1.0000
   4.500   0.9959   0.01506   0.00755  -0.0998   0.6220   1.0000
   4.750   1.0154   0.01524   0.00763  -0.0974   0.5795   1.0000
   5.000   1.0345   0.01561   0.00793  -0.0951   0.5356   1.0000
   5.250   1.0518   0.01611   0.00832  -0.0925   0.4835   1.0000
   5.500   1.0635   0.01677   0.00871  -0.0890   0.3844   1.0000
   5.750   1.0580   0.01998   0.01006  -0.0838   0.1266   1.0000
   6.000   1.0700   0.02184   0.01162  -0.0812   0.0924   1.0000
   6.250   1.0828   0.02343   0.01323  -0.0785   0.0819   1.0000
   6.500   1.0950   0.02508   0.01487  -0.0760   0.0723   1.0000
   6.750   1.1117   0.02666   0.01659  -0.0738   0.0667   1.0000
   7.000   1.1323   0.02858   0.01848  -0.0724   0.0621   1.0000
   7.250   1.1570   0.03103   0.02092  -0.0717   0.0566   1.0000
   7.500   1.1859   0.03357   0.02366  -0.0712   0.0540   1.0000
   7.750   1.2146   0.03674   0.02714  -0.0705   0.0533   1.0000
   8.000   1.2374   0.03984   0.03060  -0.0693   0.0520   1.0000
   8.250   1.2577   0.04314   0.03410  -0.0683   0.0494   1.0000
   8.500   1.2697   0.04716   0.03899  -0.0649   0.0524   1.0000
   8.750   1.2801   0.05228   0.04465  -0.0623   0.0562   1.0000
   9.000   1.2839   0.05745   0.05065  -0.0583   0.0648   1.0000
   9.250   1.2124   0.05630   0.05069  -0.0479   0.0770   1.0000
   9.500   1.1712   0.06879   0.06411  -0.0435   0.1210   1.0000
   9.750   1.1408   0.07280   0.06829  -0.0399   0.1205   1.0000
  10.000   1.1117   0.07765   0.07327  -0.0380   0.1209   1.0000
  10.250   1.0894   0.07912   0.07475  -0.0363   0.1035   1.0000
  10.500   1.0621   0.08464   0.08038  -0.0369   0.1018   1.0000
  10.750   1.0358   0.09094   0.08676  -0.0386   0.1008   1.0000
  11.000   1.0087   0.09813   0.09401  -0.0417   0.1000   1.0000
  11.250   0.9806   0.10620   0.10212  -0.0460   0.0995   1.0000
  11.500   0.9529   0.11107   0.10694  -0.0498   0.0807   1.0000
  11.750   1.0130   0.14355   0.13895  -0.0810   0.1563   1.0000
  12.000   1.0329   0.14733   0.14279  -0.0780   0.1494   1.0000
  12.250   1.0107   0.15326   0.14862  -0.0844   0.1430   1.0000
  12.500   0.8735   0.15370   0.14957  -0.0728   0.1499   1.0000
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