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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 500,000
Max Cl/Cd: 105.18 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe376-il-500000.txt
Download as CSV file: xf-goe376-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3231   0.09544   0.09328  -0.0215   1.0000   0.0157
  -7.750  -0.3299   0.09364   0.09153  -0.0210   1.0000   0.0157
  -7.500  -0.3317   0.09136   0.08929  -0.0216   1.0000   0.0157
  -7.250  -0.3305   0.08878   0.08674  -0.0231   1.0000   0.0157
  -7.000  -0.3289   0.08487   0.08286  -0.0192   1.0000   0.0160
  -6.750  -0.3302   0.08264   0.08067  -0.0177   1.0000   0.0161
  -6.500  -0.3104   0.07906   0.07709  -0.0214   0.9979   0.0165
  -6.250  -0.2793   0.07470   0.07271  -0.0290   0.9943   0.0170
  -6.000  -0.2482   0.07028   0.06826  -0.0363   0.9891   0.0177
  -5.750  -0.2053   0.06537   0.06327  -0.0471   0.9844   0.0192
  -5.500  -0.1572   0.06021   0.05796  -0.0591   0.9761   0.0195
  -5.000  -0.1057   0.05125   0.04891  -0.0667   0.9623   0.0200
  -4.750  -0.0773   0.04804   0.04565  -0.0700   0.9554   0.0204
  -4.500  -0.0445   0.04477   0.04230  -0.0742   0.9469   0.0212
  -4.250  -0.0044   0.04121   0.03862  -0.0796   0.9397   0.0225
  -4.000   0.0548   0.03761   0.03460  -0.0863   0.9314   0.0242
  -3.750   0.0892   0.03276   0.02955  -0.0903   0.9199   0.0246
  -3.500   0.1195   0.03019   0.02690  -0.0929   0.9060   0.0250
  -3.250   0.1480   0.02824   0.02480  -0.0943   0.8900   0.0257
  -3.000   0.1744   0.02646   0.02284  -0.0946   0.8733   0.0267
  -2.750   0.2003   0.02480   0.02095  -0.0944   0.8564   0.0282
  -2.500   0.2321   0.02412   0.01982  -0.0931   0.8395   0.0301
  -2.250   0.2526   0.02098   0.01640  -0.0923   0.8226   0.0308
  -2.000   0.2744   0.01952   0.01485  -0.0917   0.8054   0.0315
  -1.750   0.2976   0.01847   0.01366  -0.0910   0.7881   0.0324
  -1.500   0.3215   0.01752   0.01251  -0.0901   0.7708   0.0338
  -1.250   0.3470   0.01696   0.01167  -0.0890   0.7528   0.0366
  -1.000   0.3711   0.01579   0.01009  -0.0877   0.7347   0.0389
  -0.750   0.3942   0.01479   0.00902  -0.0870   0.7156   0.0403
  -0.500   0.4184   0.01418   0.00827  -0.0862   0.6983   0.0423
  -0.250   0.4442   0.01411   0.00801  -0.0853   0.6823   0.0468
   0.000   0.4352   0.01646   0.01234  -0.1195   0.6454   0.0371
   1.750   0.6414   0.01042   0.00325  -0.0783   0.5220   0.0557
   2.250   0.6899   0.01011   0.00274  -0.0763   0.4867   0.0448
   2.500   0.7140   0.01003   0.00258  -0.0753   0.4713   0.0436
   2.750   0.7384   0.01002   0.00250  -0.0745   0.4567   0.0437
   3.000   0.7629   0.01005   0.00247  -0.0738   0.4429   0.0441
   3.250   0.7878   0.01010   0.00249  -0.0731   0.4314   0.0461
   3.500   0.8127   0.01018   0.00253  -0.0725   0.4206   0.0463
   3.750   0.8378   0.01028   0.00257  -0.0719   0.4095   0.0466
   4.000   0.8631   0.01037   0.00264  -0.0713   0.3985   0.0474
   4.250   0.8882   0.01049   0.00274  -0.0707   0.3878   0.0510
   4.500   0.9582   0.00917   0.00317  -0.0810   0.3699   1.0000
   4.750   0.9826   0.00936   0.00331  -0.0803   0.3572   1.0000
   5.000   1.0066   0.00957   0.00346  -0.0795   0.3413   1.0000
   5.250   1.0299   0.00983   0.00363  -0.0787   0.3200   1.0000
   5.500   1.0526   0.01014   0.00382  -0.0777   0.2943   1.0000
   5.750   1.0749   0.01050   0.00406  -0.0767   0.2721   1.0000
   6.000   1.0973   0.01084   0.00432  -0.0758   0.2533   1.0000
   6.250   1.1197   0.01119   0.00461  -0.0748   0.2373   1.0000
   6.500   1.1421   0.01154   0.00491  -0.0739   0.2229   1.0000
   6.750   1.1642   0.01190   0.00521  -0.0729   0.2071   1.0000
   7.000   1.1856   0.01233   0.00554  -0.0718   0.1878   1.0000
   7.250   1.2071   0.01274   0.00588  -0.0708   0.1656   1.0000
   7.500   1.2262   0.01337   0.00631  -0.0694   0.1342   1.0000
   7.750   1.2424   0.01426   0.00693  -0.0676   0.0936   1.0000
   8.250   1.2666   0.01675   0.00896  -0.0627   0.0192   1.0000
   8.500   1.2849   0.01742   0.00975  -0.0610   0.0172   1.0000
   8.750   1.3031   0.01806   0.01049  -0.0594   0.0165   1.0000
   9.000   1.3200   0.01877   0.01131  -0.0576   0.0158   1.0000
   9.250   1.3354   0.01957   0.01221  -0.0557   0.0153   1.0000
   9.500   1.3479   0.02054   0.01327  -0.0533   0.0143   1.0000
   9.750   1.3584   0.02156   0.01441  -0.0507   0.0137   1.0000
  10.000   1.3624   0.02282   0.01577  -0.0471   0.0131   1.0000
  10.250   1.3602   0.02427   0.01733  -0.0426   0.0127   1.0000
  10.500   1.3578   0.02585   0.01903  -0.0385   0.0125   1.0000
  10.750   1.3578   0.02742   0.02071  -0.0352   0.0123   1.0000
  11.000   1.3625   0.02877   0.02216  -0.0327   0.0121   1.0000
  11.250   1.3665   0.03028   0.02377  -0.0305   0.0119   1.0000
  11.500   1.3690   0.03203   0.02563  -0.0285   0.0117   1.0000
  11.750   1.3700   0.03404   0.02776  -0.0266   0.0117   1.0000
  12.000   1.3714   0.03617   0.02999  -0.0251   0.0116   1.0000
  12.250   1.3733   0.03835   0.03229  -0.0238   0.0114   1.0000
  12.500   1.3743   0.04075   0.03479  -0.0227   0.0112   1.0000
  12.750   1.3757   0.04319   0.03734  -0.0218   0.0110   1.0000
  13.000   1.3762   0.04582   0.04009  -0.0209   0.0109   1.0000
  13.250   1.3773   0.04840   0.04277  -0.0205   0.0106   1.0000
  13.500   1.3768   0.05131   0.04579  -0.0199   0.0104   1.0000
  13.750   1.3768   0.05408   0.04864  -0.0199   0.0100   1.0000
  14.000   1.3763   0.05706   0.05172  -0.0196   0.0099   1.0000
  14.250   1.3744   0.06032   0.05512  -0.0193   0.0099   1.0000
  14.500   1.3721   0.06359   0.05849  -0.0195   0.0097   1.0000
  14.750   1.3690   0.06717   0.06220  -0.0195   0.0097   1.0000
  15.000   1.3638   0.07110   0.06629  -0.0201   0.0097   1.0000
  15.250   1.3585   0.07509   0.07040  -0.0208   0.0096   1.0000
  15.500   1.3444   0.08084   0.07641  -0.0227   0.0099   1.0000
  15.750   1.3315   0.08651   0.08229  -0.0247   0.0100   1.0000
  16.000   1.3192   0.09224   0.08820  -0.0271   0.0101   1.0000
  16.250   1.3058   0.09841   0.09455  -0.0299   0.0101   1.0000
  16.500   1.2860   0.10613   0.10250  -0.0336   0.0104   1.0000
  16.750   1.2696   0.11337   0.10992  -0.0373   0.0107   1.0000
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