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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.87 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe403-il-1000000-n5.txt
Download as CSV file: xf-goe403-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3596   0.09567   0.09412  -0.0238   1.0000   0.0021
  -8.500  -0.3605   0.09151   0.08998  -0.0247   1.0000   0.0023
  -8.250  -0.3606   0.08822   0.08672  -0.0254   1.0000   0.0023
  -8.000  -0.3576   0.08408   0.08261  -0.0277   0.9988   0.0023
  -7.500  -0.3303   0.07502   0.07356  -0.0387   0.9708   0.0026
  -7.000  -0.2977   0.01783   0.01455  -0.0978   0.8747   0.0024
  -6.750  -0.2775   0.01485   0.01098  -0.0976   0.8516   0.0025
  -6.500  -0.2537   0.01361   0.00947  -0.0973   0.8361   0.0028
  -6.250  -0.2286   0.01286   0.00853  -0.0971   0.8253   0.0030
  -5.750  -0.1772   0.01127   0.00648  -0.0965   0.8089   0.0034
  -5.500  -0.1511   0.01062   0.00562  -0.0962   0.8015   0.0037
  -5.250  -0.1244   0.01013   0.00499  -0.0960   0.7946   0.0040
  -5.000  -0.0981   0.00954   0.00421  -0.0957   0.7875   0.0045
  -4.750  -0.0713   0.00908   0.00364  -0.0955   0.7805   0.0052
  -4.250  -0.0174   0.00847   0.00282  -0.0950   0.7658   0.0072
  -4.000   0.0094   0.00814   0.00243  -0.0948   0.7582   0.0102
  -3.750   0.0364   0.00792   0.00222  -0.0946   0.7493   0.0184
  -3.500   0.0636   0.00779   0.00204  -0.0944   0.7399   0.0229
  -3.250   0.0907   0.00772   0.00193  -0.0942   0.7290   0.0277
  -3.000   0.1179   0.00769   0.00183  -0.0940   0.7161   0.0303
  -2.750   0.1450   0.00771   0.00179  -0.0938   0.7012   0.0318
  -2.500   0.1719   0.00769   0.00168  -0.0936   0.6825   0.0327
  -2.000   0.2245   0.00755   0.00126  -0.0929   0.6341   0.0348
  -1.750   0.2508   0.00755   0.00113  -0.0925   0.6071   0.0357
  -1.500   0.2772   0.00758   0.00102  -0.0922   0.5819   0.0365
  -1.250   0.3038   0.00760   0.00094  -0.0919   0.5615   0.0375
  -1.000   0.3305   0.00761   0.00088  -0.0917   0.5446   0.0389
  -0.750   0.3574   0.00762   0.00083  -0.0915   0.5308   0.0415
  -0.500   0.3844   0.00761   0.00079  -0.0913   0.5190   0.0492
  -0.250   0.4113   0.00756   0.00078  -0.0912   0.5088   0.0710
   0.000   0.4383   0.00755   0.00079  -0.0910   0.4994   0.0907
   0.250   0.4654   0.00757   0.00079  -0.0909   0.4906   0.1012
   0.500   0.4926   0.00758   0.00081  -0.0908   0.4831   0.1103
   1.000   0.5468   0.00759   0.00086  -0.0905   0.4664   0.1416
   1.250   0.5736   0.00759   0.00091  -0.0903   0.4577   0.1695
   1.500   0.6003   0.00754   0.00098  -0.0902   0.4481   0.2293
   1.750   0.6269   0.00750   0.00106  -0.0901   0.4375   0.2908
   2.000   0.6456   0.00654   0.00125  -0.0887   0.4144   0.7986
   2.500   0.7098   0.00658   0.00145  -0.0908   0.3634   1.0000
   2.750   0.7336   0.00699   0.00161  -0.0901   0.3124   1.0000
   3.000   0.7516   0.00811   0.00207  -0.0887   0.1781   1.0000
   3.250   0.7689   0.00942   0.00274  -0.0871   0.0174   1.0000
   3.500   0.7949   0.00962   0.00296  -0.0867   0.0116   1.0000
   3.750   0.8208   0.00982   0.00318  -0.0864   0.0099   1.0000
   4.000   0.8464   0.01006   0.00345  -0.0860   0.0082   1.0000
   4.250   0.8713   0.01041   0.00384  -0.0854   0.0066   1.0000
   4.500   0.8968   0.01065   0.00411  -0.0850   0.0056   1.0000
   4.750   0.9217   0.01097   0.00444  -0.0845   0.0050   1.0000
   5.000   0.9454   0.01143   0.00494  -0.0838   0.0043   1.0000
   5.250   0.9690   0.01192   0.00550  -0.0830   0.0040   1.0000
   5.500   0.9922   0.01245   0.00610  -0.0822   0.0036   1.0000
   5.750   1.0159   0.01287   0.00657  -0.0815   0.0031   1.0000
   6.000   1.0394   0.01328   0.00701  -0.0809   0.0028   1.0000
   6.250   1.0620   0.01380   0.00756  -0.0801   0.0026   1.0000
   6.500   1.0796   0.01489   0.00876  -0.0784   0.0024   1.0000
   6.750   1.0996   0.01566   0.00962  -0.0771   0.0023   1.0000
   7.000   1.1166   0.01677   0.01085  -0.0753   0.0021   1.0000
   7.250   1.1307   0.01837   0.01257  -0.0729   0.0019   1.0000
   7.500   1.1458   0.02041   0.01472  -0.0705   0.0017   1.0000
   7.750   1.1650   0.02268   0.01716  -0.0689   0.0017   1.0000
   8.000   1.1865   0.02518   0.01981  -0.0676   0.0017   1.0000
   8.250   1.2072   0.02781   0.02263  -0.0662   0.0018   1.0000
   8.500   1.2253   0.03068   0.02574  -0.0645   0.0018   1.0000
   8.750   1.2404   0.03359   0.02890  -0.0625   0.0019   1.0000
   9.000   1.2546   0.03609   0.03162  -0.0606   0.0017   1.0000
   9.250   1.2653   0.03886   0.03463  -0.0583   0.0017   1.0000
   9.500   1.2751   0.04086   0.03679  -0.0564   0.0015   1.0000
   9.750   1.2804   0.04371   0.03986  -0.0538   0.0015   1.0000
  10.000   1.2817   0.04675   0.04313  -0.0509   0.0015   1.0000
  10.250   1.2786   0.04980   0.04640  -0.0478   0.0015   1.0000
  10.500   1.2745   0.05131   0.04801  -0.0446   0.0014   1.0000
  10.750   1.2566   0.05506   0.05199  -0.0400   0.0014   1.0000
  11.000   1.2450   0.05722   0.05427  -0.0373   0.0014   1.0000
  11.250   1.2279   0.06083   0.05804  -0.0352   0.0014   1.0000
  11.500   1.2163   0.06357   0.06089  -0.0344   0.0014   1.0000
  11.750   1.1989   0.06788   0.06534  -0.0343   0.0014   1.0000
  12.000   1.1692   0.07508   0.07277  -0.0353   0.0015   1.0000
  12.250   1.1534   0.08004   0.07785  -0.0374   0.0014   1.0000
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