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GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 438 AIRFOIL (goe438-il)
Reynolds number: 50,000
Max Cl/Cd: 24.65 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe438-il-50000.txt
Download as CSV file: xf-goe438-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 438 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3504   0.11003   0.10290  -0.0262   1.0000   0.2359
  -8.750  -0.3259   0.10477   0.09760  -0.0244   1.0000   0.2479
  -8.500  -0.3602   0.10588   0.09894  -0.0247   1.0000   0.2530
  -8.250  -0.3352   0.10084   0.09386  -0.0229   1.0000   0.2678
  -8.000  -0.3241   0.09715   0.09021  -0.0215   1.0000   0.2776
  -7.750  -0.3557   0.09769   0.09096  -0.0200   1.0000   0.2860
  -7.500  -0.3382   0.09370   0.08698  -0.0182   1.0000   0.3009
  -7.250  -0.3327   0.09088   0.08423  -0.0160   1.0000   0.3154
  -7.000  -0.3792   0.09201   0.08562  -0.0122   1.0000   0.3197
  -6.750  -0.3425   0.08683   0.08039  -0.0107   1.0000   0.3421
  -6.500  -0.3772   0.08713   0.08089  -0.0061   1.0000   0.3524
  -6.250  -0.3792   0.08494   0.07879  -0.0028   1.0000   0.3688
  -6.000  -0.3862   0.08311   0.07706   0.0007   1.0000   0.3856
  -5.750  -0.3987   0.08167   0.07573   0.0044   1.0000   0.4030
  -5.500  -0.3746   0.07822   0.07227   0.0080   1.0000   0.4302
  -5.250  -0.3999   0.07769   0.07188   0.0129   1.0000   0.4528
  -5.000  -0.3995   0.07591   0.07018   0.0180   1.0000   0.4865
  -4.750  -0.3516   0.07195   0.06617   0.0209   1.0000   0.5450
  -4.500  -0.3128   0.06894   0.06311   0.0236   1.0000   0.6172
  -4.250   0.0956   0.04616   0.03921  -0.0330   1.0000   1.0000
  -4.000   0.0986   0.04506   0.03820  -0.0321   1.0000   1.0000
  -3.750   0.0340   0.04799   0.04143  -0.0158   1.0000   0.9713
  -3.500  -0.0498   0.05127   0.04505   0.0026   1.0000   0.9244
  -3.250  -0.1282   0.05352   0.04758   0.0173   1.0000   0.8753
  -3.000  -0.1990   0.05475   0.04908   0.0287   1.0000   0.8293
  -2.750  -0.3087   0.04475   0.03699  -0.0233   1.0000   0.2514
  -2.500  -0.2845   0.04217   0.03402  -0.0247   1.0000   0.2303
  -2.250  -0.2602   0.04025   0.03156  -0.0256   1.0000   0.2155
  -2.000  -0.2386   0.03867   0.02957  -0.0259   1.0000   0.2073
  -1.750  -0.2064   0.03789   0.02818  -0.0278   0.9961   0.2034
  -1.500  -0.1525   0.03705   0.02690  -0.0334   0.9826   0.2028
  -1.250  -0.1038   0.03618   0.02574  -0.0378   0.9683   0.2017
  -1.000  -0.0560   0.03561   0.02486  -0.0419   0.9534   0.2020
  -0.750  -0.0089   0.03504   0.02418  -0.0459   0.9383   0.2075
  -0.500   0.0369   0.03470   0.02372  -0.0493   0.9228   0.2149
  -0.250   0.0851   0.03441   0.02325  -0.0528   0.9073   0.2213
   0.000   0.1332   0.03407   0.02289  -0.0562   0.8916   0.2326
   0.250   0.1780   0.03371   0.02262  -0.0591   0.8758   0.2546
   0.500   0.2216   0.03307   0.02234  -0.0617   0.8603   0.2967
   0.750   0.2983   0.03062   0.02161  -0.0686   0.8466   1.0000
   1.000   0.3416   0.03090   0.02153  -0.0708   0.8301   1.0000
   1.250   0.3850   0.03105   0.02146  -0.0730   0.8135   1.0000
   1.500   0.4266   0.03117   0.02141  -0.0748   0.7973   1.0000
   1.750   0.4672   0.03120   0.02132  -0.0762   0.7810   1.0000
   2.000   0.5035   0.03128   0.02129  -0.0769   0.7650   1.0000
   2.250   0.5387   0.03132   0.02125  -0.0773   0.7490   1.0000
   2.500   0.5713   0.03142   0.02128  -0.0773   0.7332   1.0000
   2.750   0.6019   0.03159   0.02138  -0.0770   0.7177   1.0000
   3.000   0.6312   0.03179   0.02154  -0.0765   0.7024   1.0000
   3.250   0.6583   0.03212   0.02183  -0.0758   0.6874   1.0000
   3.500   0.6833   0.03258   0.02227  -0.0749   0.6726   1.0000
   3.750   0.7071   0.03315   0.02282  -0.0739   0.6583   1.0000
   4.000   0.7302   0.03382   0.02348  -0.0729   0.6447   1.0000
   4.250   0.7586   0.03423   0.02388  -0.0723   0.6324   1.0000
   4.500   0.7971   0.03407   0.02371  -0.0727   0.6215   1.0000
   4.750   0.8058   0.03569   0.02536  -0.0705   0.6077   1.0000
   5.000   0.8160   0.03731   0.02702  -0.0686   0.5949   1.0000
   5.250   0.8426   0.03797   0.02770  -0.0680   0.5844   1.0000
   5.500   0.8653   0.03887   0.02866  -0.0671   0.5737   1.0000
   5.750   0.8603   0.04164   0.03149  -0.0644   0.5615   1.0000
   6.000   0.8801   0.04284   0.03274  -0.0633   0.5518   1.0000
   6.250   0.8954   0.04434   0.03430  -0.0621   0.5418   1.0000
   6.500   0.8642   0.04930   0.03929  -0.0585   0.5306   1.0000
   6.750   0.9367   0.04668   0.03677  -0.0601   0.5230   1.0000
   7.000   0.8495   0.05596   0.04600  -0.0545   0.5117   1.0000
   7.250   0.8268   0.06116   0.05120  -0.0534   0.5029   1.0000
   7.500   0.8475   0.06244   0.05257  -0.0525   0.4937   1.0000
   7.750   0.8089   0.06925   0.05934  -0.0521   0.4863   1.0000
   8.000   0.8699   0.06688   0.05713  -0.0508   0.4761   1.0000
   8.250   0.8048   0.07631   0.06647  -0.0513   0.4704   1.0000
   8.500   0.8598   0.07477   0.06510  -0.0500   0.4599   1.0000
   8.750   0.8075   0.08317   0.07343  -0.0510   0.4562   1.0000
   9.000   0.7911   0.08837   0.07866  -0.0516   0.4529   1.0000
   9.250   0.8192   0.08965   0.08005  -0.0508   0.4426   1.0000
   9.500   0.8001   0.09535   0.08577  -0.0519   0.4412   1.0000
   9.750   0.7984   0.10022   0.09071  -0.0531   0.4427   1.0000
  10.000   0.8045   0.10482   0.09539  -0.0542   0.4441   1.0000
  11.500   1.3206   0.05357   0.04539  -0.0265   0.2559   1.0000
  11.750   1.2728   0.05854   0.05062  -0.0209   0.2538   1.0000
  12.000   1.2161   0.06578   0.05802  -0.0181   0.2539   1.0000
  12.250   1.1452   0.07726   0.06953  -0.0196   0.2560   1.0000
  12.500   1.1428   0.07967   0.07198  -0.0184   0.2410   1.0000
  12.750   1.2253   0.07082   0.06311  -0.0125   0.2104   1.0000
  13.000   0.8951   0.13318   0.12481  -0.0462   0.2535   1.0000
  13.250   0.8746   0.14105   0.13267  -0.0497   0.2504   1.0000
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