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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 100,000
Max Cl/Cd: 55.86 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe682-il-100000.txt
Download as CSV file: xf-goe682-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 682 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3090   0.10109   0.09614  -0.0353   1.0000   0.1127
  -8.500  -0.3319   0.10058   0.09578  -0.0360   1.0000   0.1156
  -8.250  -0.3638   0.10069   0.09606  -0.0348   1.0000   0.1162
  -8.000  -0.3473   0.09566   0.09103  -0.0326   1.0000   0.1186
  -7.750  -0.3370   0.09304   0.08844  -0.0298   1.0000   0.1216
  -7.500  -0.3471   0.09170   0.08718  -0.0270   1.0000   0.1239
  -7.250  -0.3665   0.09087   0.08646  -0.0236   1.0000   0.1260
  -7.000  -0.3898   0.09018   0.08588  -0.0205   1.0000   0.1275
  -6.750  -0.4183   0.08932   0.08514  -0.0214   1.0000   0.1300
  -6.500  -0.4451   0.08683   0.08267  -0.0275   1.0000   0.1318
  -6.250  -0.4392   0.08404   0.07997  -0.0211   1.0000   0.1332
  -6.000  -0.4331   0.08199   0.07794  -0.0177   0.9993   0.1358
  -5.750  -0.4001   0.07595   0.07174  -0.0335   0.9891   0.1478
  -5.500  -0.3654   0.07272   0.06832  -0.0420   0.9811   0.1614
  -5.250  -0.3454   0.06841   0.06409  -0.0414   0.9749   0.1645
  -4.750  -0.2769   0.06178   0.05699  -0.0564   0.9581   0.1933
  -4.500  -0.2571   0.05770   0.05306  -0.0556   0.9514   0.1966
  -4.250  -0.2240   0.05453   0.04974  -0.0601   0.9437   0.2123
  -4.000  -0.1714   0.03895   0.03256  -0.0744   0.9377   0.1194
  -3.750  -0.1366   0.03478   0.02782  -0.0768   0.9301   0.1101
  -3.500  -0.0913   0.03172   0.02418  -0.0806   0.9256   0.1099
  -3.250  -0.0646   0.02979   0.02182  -0.0807   0.9156   0.1099
  -3.000  -0.0196   0.02779   0.01935  -0.0836   0.9109   0.1109
  -2.750   0.0078   0.02674   0.01799  -0.0835   0.9012   0.1137
  -2.500   0.0512   0.02546   0.01652  -0.0862   0.8962   0.1200
  -2.250   0.0796   0.02479   0.01579  -0.0862   0.8870   0.1253
  -2.000   0.1222   0.02378   0.01468  -0.0885   0.8815   0.1344
  -1.750   0.1541   0.02327   0.01418  -0.0890   0.8735   0.1480
  -1.500   0.1930   0.02251   0.01358  -0.0908   0.8670   0.1682
  -1.250   0.2406   0.02150   0.01279  -0.0938   0.8635   0.2259
  -1.000   0.2611   0.02090   0.01265  -0.0925   0.8525   0.3124
  -0.750   0.3039   0.01973   0.01207  -0.0948   0.8484   0.4434
  -0.500   0.3782   0.01801   0.01162  -0.1025   0.8447   1.0000
  -0.250   0.4089   0.01801   0.01139  -0.1027   0.8353   1.0000
   0.000   0.4384   0.01805   0.01124  -0.1026   0.8260   1.0000
   0.250   0.4743   0.01788   0.01091  -0.1035   0.8183   1.0000
   0.500   0.4991   0.01802   0.01093  -0.1026   0.8074   1.0000
   0.750   0.5379   0.01774   0.01050  -0.1038   0.8008   1.0000
   1.000   0.5603   0.01793   0.01060  -0.1025   0.7887   1.0000
   1.250   0.5879   0.01793   0.01051  -0.1019   0.7778   1.0000
   1.500   0.6253   0.01752   0.00996  -0.1025   0.7688   1.0000
   1.750   0.6509   0.01741   0.00976  -0.1013   0.7546   1.0000
   2.000   0.6772   0.01729   0.00955  -0.1002   0.7402   1.0000
   2.250   0.7030   0.01727   0.00946  -0.0991   0.7266   1.0000
   2.500   0.7292   0.01733   0.00945  -0.0983   0.7143   1.0000
   2.750   0.7576   0.01732   0.00936  -0.0978   0.7028   1.0000
   3.000   0.7856   0.01733   0.00930  -0.0972   0.6909   1.0000
   3.250   0.8096   0.01749   0.00942  -0.0961   0.6772   1.0000
   3.500   0.8342   0.01764   0.00955  -0.0951   0.6636   1.0000
   3.750   0.8593   0.01779   0.00966  -0.0942   0.6503   1.0000
   4.000   0.8849   0.01793   0.00975  -0.0933   0.6370   1.0000
   4.250   0.9108   0.01805   0.00983  -0.0925   0.6233   1.0000
   4.500   0.9364   0.01817   0.00991  -0.0916   0.6092   1.0000
   4.750   0.9618   0.01832   0.01000  -0.0907   0.5948   1.0000
   5.000   0.9862   0.01849   0.01016  -0.0897   0.5797   1.0000
   5.250   1.0094   0.01869   0.01035  -0.0885   0.5635   1.0000
   5.500   1.0313   0.01891   0.01057  -0.0871   0.5459   1.0000
   5.750   1.0530   0.01914   0.01080  -0.0857   0.5274   1.0000
   6.000   1.0753   0.01939   0.01103  -0.0844   0.5085   1.0000
   6.250   1.0982   0.01969   0.01126  -0.0832   0.4896   1.0000
   6.500   1.1217   0.02008   0.01152  -0.0821   0.4708   1.0000
   6.750   1.1416   0.02061   0.01206  -0.0806   0.4507   1.0000
   7.000   1.1630   0.02119   0.01259  -0.0793   0.4323   1.0000
   7.250   1.1851   0.02185   0.01321  -0.0783   0.4162   1.0000
   7.500   1.2074   0.02256   0.01390  -0.0773   0.4018   1.0000
   7.750   1.2294   0.02323   0.01458  -0.0763   0.3883   1.0000
   8.000   1.2517   0.02387   0.01518  -0.0753   0.3754   1.0000
   8.250   1.2733   0.02446   0.01575  -0.0743   0.3627   1.0000
   8.500   1.2910   0.02507   0.01649  -0.0726   0.3502   1.0000
   8.750   1.3107   0.02580   0.01733  -0.0714   0.3398   1.0000
   9.000   1.3337   0.02647   0.01799  -0.0706   0.3299   1.0000
   9.250   1.3513   0.02704   0.01864  -0.0690   0.3183   1.0000
   9.500   1.3654   0.02757   0.01927  -0.0668   0.3054   1.0000
   9.750   1.3770   0.02797   0.01973  -0.0643   0.2908   1.0000
  10.000   1.3855   0.02839   0.02016  -0.0614   0.2756   1.0000
  10.250   1.3932   0.02895   0.02077  -0.0584   0.2616   1.0000
  10.500   1.4013   0.02964   0.02154  -0.0556   0.2492   1.0000
  10.750   1.4072   0.03035   0.02229  -0.0525   0.2373   1.0000
  11.000   1.4101   0.03110   0.02308  -0.0490   0.2253   1.0000
  11.250   1.4077   0.03197   0.02409  -0.0450   0.2128   1.0000
  11.500   1.4025   0.03304   0.02532  -0.0411   0.1991   1.0000
  11.750   1.3943   0.03441   0.02679  -0.0375   0.1831   1.0000
  12.000   1.3826   0.03630   0.02883  -0.0342   0.1604   1.0000
  12.250   1.3658   0.03913   0.03157  -0.0315   0.1312   1.0000
  12.500   1.3468   0.04284   0.03505  -0.0293   0.1074   1.0000
  12.750   1.3303   0.04679   0.03884  -0.0278   0.0935   1.0000
  13.000   1.3179   0.05061   0.04260  -0.0266   0.0842   1.0000
  13.250   1.3070   0.05440   0.04627  -0.0258   0.0779   1.0000
  13.500   1.3035   0.05764   0.04965  -0.0251   0.0719   1.0000
  13.750   1.3004   0.06080   0.05270  -0.0244   0.0675   1.0000
  14.000   1.3022   0.06367   0.05573  -0.0237   0.0636   1.0000
  14.250   1.3068   0.06623   0.05836  -0.0230   0.0604   1.0000
  14.500   1.3233   0.06771   0.05963  -0.0214   0.0568   1.0000
  14.750   1.3256   0.07074   0.06293  -0.0211   0.0550   1.0000
  15.000   1.3266   0.07396   0.06635  -0.0211   0.0529   1.0000
  15.250   1.3297   0.07698   0.06950  -0.0210   0.0511   1.0000
  15.500   1.3381   0.07954   0.07210  -0.0205   0.0493   1.0000
  15.750   1.3621   0.08166   0.07420  -0.0190   0.0476   1.0000
  16.000   1.3539   0.08612   0.07895  -0.0197   0.0473   1.0000
  16.250   1.3428   0.09105   0.08416  -0.0209   0.0471   1.0000
  16.500   1.3290   0.09648   0.08987  -0.0226   0.0469   1.0000
  16.750   1.3130   0.10242   0.09607  -0.0249   0.0469   1.0000
  17.000   1.2948   0.10896   0.10286  -0.0279   0.0469   1.0000
  17.250   1.2751   0.11606   0.11020  -0.0315   0.0470   1.0000
  17.500   1.2532   0.12391   0.11827  -0.0360   0.0472   1.0000
  17.750   1.2314   0.13225   0.12681  -0.0410   0.0475   1.0000
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