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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 100,000
Max Cl/Cd: 57.64 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe115-il-100000-n5.txt
Download as CSV file: xf-goe115-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3776   0.09087   0.08607  -0.0408   1.0000   0.0320
  -8.750  -0.3804   0.08679   0.08207  -0.0421   1.0000   0.0308
  -8.250  -0.4139   0.07306   0.06858  -0.0493   1.0000   0.0265
  -8.000  -0.4234   0.06913   0.06475  -0.0502   1.0000   0.0263
  -7.750  -0.4320   0.06467   0.06036  -0.0524   1.0000   0.0260
  -7.500  -0.4420   0.05965   0.05535  -0.0554   1.0000   0.0257
  -7.250  -0.4409   0.05314   0.04863  -0.0617   0.9950   0.0254
  -7.000  -0.4186   0.04536   0.04024  -0.0715   0.9824   0.0254
  -6.750  -0.3930   0.03966   0.03381  -0.0772   0.9713   0.0258
  -6.500  -0.3653   0.03513   0.02853  -0.0811   0.9620   0.0275
  -6.250  -0.3364   0.03222   0.02546  -0.0836   0.9537   0.0299
  -6.000  -0.3061   0.02932   0.02202  -0.0854   0.9447   0.0314
  -5.750  -0.2724   0.02685   0.01900  -0.0872   0.9375   0.0334
  -5.500  -0.2425   0.02485   0.01654  -0.0881   0.9275   0.0366
  -5.250  -0.2113   0.02291   0.01444  -0.0891   0.9190   0.0388
  -5.000  -0.1793   0.02158   0.01295  -0.0901   0.9102   0.0425
  -4.750  -0.1494   0.02057   0.01175  -0.0904   0.8997   0.0454
  -4.500  -0.1201   0.01937   0.01048  -0.0909   0.8899   0.0474
  -4.250  -0.0896   0.01854   0.00954  -0.0916   0.8803   0.0522
  -4.000  -0.0610   0.01793   0.00870  -0.0917   0.8687   0.0550
  -3.750  -0.0319   0.01740   0.00794  -0.0919   0.8575   0.0571
  -3.500  -0.0028   0.01680   0.00719  -0.0921   0.8469   0.0610
  -3.250   0.0269   0.01633   0.00652  -0.0924   0.8371   0.0677
  -3.000   0.0540   0.01571   0.00595  -0.0923   0.8258   0.0907
  -2.750   0.0801   0.01511   0.00595  -0.0923   0.8149   0.2422
  -2.500   0.1086   0.01518   0.00588  -0.0923   0.8047   0.2822
  -2.250   0.1370   0.01515   0.00567  -0.0922   0.7949   0.2972
  -2.000   0.1641   0.01515   0.00556  -0.0919   0.7843   0.3137
  -1.750   0.1918   0.01512   0.00539  -0.0918   0.7753   0.3235
  -1.500   0.2195   0.01508   0.00523  -0.0917   0.7667   0.3336
  -1.250   0.2463   0.01506   0.00517  -0.0915   0.7574   0.3478
  -0.750   0.3006   0.01499   0.00503  -0.0912   0.7409   0.3773
  -0.500   0.3278   0.01495   0.00499  -0.0910   0.7339   0.3955
  -0.250   0.3542   0.01489   0.00502  -0.0908   0.7264   0.4193
   0.250   0.4089   0.01482   0.00501  -0.0906   0.7130   0.4519
   0.500   0.4367   0.01476   0.00499  -0.0905   0.7074   0.4697
   0.750   0.4629   0.01472   0.00510  -0.0903   0.7005   0.4986
   1.000   0.4891   0.01455   0.00518  -0.0900   0.6951   0.5616
   1.500   0.5603   0.01390   0.00539  -0.0929   0.6841   1.0000
   1.750   0.5875   0.01407   0.00548  -0.0927   0.6792   1.0000
   2.000   0.6134   0.01429   0.00569  -0.0925   0.6729   1.0000
   2.250   0.6399   0.01448   0.00586  -0.0922   0.6665   1.0000
   2.500   0.6658   0.01467   0.00604  -0.0917   0.6592   1.0000
   2.750   0.6919   0.01484   0.00620  -0.0913   0.6514   1.0000
   3.000   0.7173   0.01504   0.00645  -0.0908   0.6433   1.0000
   3.250   0.7437   0.01523   0.00666  -0.0904   0.6365   1.0000
   3.500   0.7693   0.01548   0.00700  -0.0901   0.6303   1.0000
   3.750   0.7951   0.01573   0.00736  -0.0897   0.6241   1.0000
   4.000   0.8216   0.01597   0.00768  -0.0894   0.6187   1.0000
   4.250   0.8464   0.01626   0.00813  -0.0889   0.6116   1.0000
   4.500   0.8733   0.01649   0.00845  -0.0885   0.6057   1.0000
   4.750   0.8972   0.01660   0.00871  -0.0875   0.5916   1.0000
   5.000   0.9182   0.01657   0.00877  -0.0857   0.5664   1.0000
   5.250   0.9364   0.01643   0.00861  -0.0832   0.5239   1.0000
   5.500   0.9528   0.01653   0.00864  -0.0806   0.4622   1.0000
   5.750   0.9533   0.01797   0.00898  -0.0759   0.2900   1.0000
   6.000   0.9390   0.02149   0.01093  -0.0706   0.0655   1.0000
   6.250   0.9504   0.02289   0.01235  -0.0680   0.0470   1.0000
   6.500   0.9620   0.02417   0.01372  -0.0656   0.0390   1.0000
   6.750   0.9748   0.02527   0.01495  -0.0634   0.0337   1.0000
   7.000   0.9814   0.02676   0.01655  -0.0605   0.0312   1.0000
   7.250   0.9895   0.02799   0.01793  -0.0577   0.0294   1.0000
   7.500   0.9973   0.02922   0.01929  -0.0549   0.0271   1.0000
   7.750   1.0053   0.03053   0.02067  -0.0523   0.0249   1.0000
   8.000   1.0139   0.03207   0.02224  -0.0500   0.0235   1.0000
   8.250   1.0268   0.03388   0.02407  -0.0481   0.0224   1.0000
   8.500   1.0562   0.03640   0.02657  -0.0481   0.0213   1.0000
   8.750   1.0823   0.03816   0.02855  -0.0476   0.0202   1.0000
   9.000   1.1081   0.04024   0.03090  -0.0472   0.0185   1.0000
   9.250   1.1359   0.04310   0.03406  -0.0471   0.0180   1.0000
   9.500   1.1556   0.04608   0.03737  -0.0461   0.0176   1.0000
   9.750   1.1689   0.04911   0.04076  -0.0444   0.0174   1.0000
  10.000   1.1757   0.05222   0.04423  -0.0421   0.0173   1.0000
  10.250   1.1768   0.05524   0.04758  -0.0394   0.0172   1.0000
  10.500   1.1736   0.05820   0.05084  -0.0366   0.0171   1.0000
  10.750   1.1667   0.06116   0.05409  -0.0339   0.0168   1.0000
  11.000   1.1576   0.06437   0.05763  -0.0316   0.0168   1.0000
  11.250   1.1462   0.06770   0.06122  -0.0298   0.0165   1.0000
  11.500   1.1327   0.07143   0.06519  -0.0286   0.0165   1.0000
  11.750   1.1178   0.07545   0.06944  -0.0281   0.0163   1.0000
  12.000   1.1017   0.07991   0.07413  -0.0283   0.0164   1.0000
  12.250   1.0840   0.08481   0.07922  -0.0292   0.0163   1.0000
  12.500   1.0650   0.09032   0.08493  -0.0310   0.0163   1.0000
  12.750   1.0450   0.09655   0.09135  -0.0335   0.0167   1.0000
  13.000   1.0250   0.10318   0.09809  -0.0368   0.0167   1.0000
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