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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 100,000
Max Cl/Cd: 57.97 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe116-il-100000.txt
Download as CSV file: xf-goe116-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3614   0.09661   0.09216  -0.0336   1.0000   0.1121
  -8.000  -0.3902   0.09626   0.09209  -0.0409   1.0000   0.1146
  -7.750  -0.3940   0.09279   0.08876  -0.0427   1.0000   0.1150
  -7.000  -0.3538   0.06332   0.05976  -0.0466   0.9827   0.0624
  -6.750  -0.4387   0.07194   0.06816  -0.0454   0.9948   0.0646
  -6.500  -0.4147   0.05528   0.05120  -0.0634   0.9860   0.0523
  -6.250  -0.3874   0.03907   0.03407  -0.0783   0.9792   0.0468
  -6.000  -0.3510   0.03069   0.02420  -0.0849   0.9733   0.0436
  -5.750  -0.3085   0.02743   0.02028  -0.0887   0.9691   0.0432
  -5.500  -0.2742   0.02526   0.01786  -0.0908   0.9618   0.0456
  -5.250  -0.2323   0.02357   0.01582  -0.0939   0.9570   0.0503
  -5.000  -0.1945   0.02226   0.01420  -0.0960   0.9506   0.0531
  -4.750  -0.1542   0.02084   0.01263  -0.0987   0.9450   0.0610
  -4.500  -0.1096   0.02096   0.01303  -0.1016   0.9398   0.1349
  -4.250  -0.0759   0.02371   0.01556  -0.1025   0.9307   0.1832
  -4.000  -0.0408   0.02415   0.01595  -0.1041   0.9247   0.2008
  -3.750  -0.0090   0.02462   0.01625  -0.1053   0.9173   0.2234
  -3.500   0.0269   0.02432   0.01579  -0.1071   0.9123   0.2379
  -3.250   0.0526   0.02415   0.01577  -0.1073   0.9044   0.2570
  -3.000   0.0903   0.02367   0.01487  -0.1093   0.9000   0.2654
  -2.750   0.1159   0.02313   0.01421  -0.1094   0.8916   0.2674
  -2.500   0.1502   0.02252   0.01346  -0.1107   0.8869   0.2704
  -2.250   0.1763   0.02230   0.01310  -0.1107   0.8791   0.2739
  -2.000   0.2087   0.02191   0.01250  -0.1115   0.8738   0.2762
  -1.750   0.2355   0.02177   0.01222  -0.1116   0.8668   0.2779
  -1.500   0.2655   0.02150   0.01183  -0.1120   0.8610   0.2799
  -1.250   0.2929   0.02130   0.01162  -0.1122   0.8548   0.2828
  -1.000   0.3203   0.02118   0.01148  -0.1122   0.8483   0.2871
  -0.750   0.3501   0.02103   0.01125  -0.1125   0.8435   0.2916
  -0.500   0.3744   0.02110   0.01136  -0.1122   0.8359   0.2950
  -0.250   0.4040   0.02087   0.01118  -0.1123   0.8313   0.2995
   0.000   0.4275   0.02109   0.01145  -0.1121   0.8238   0.3043
   0.250   0.4557   0.02098   0.01140  -0.1120   0.8187   0.3104
   0.500   0.4799   0.02117   0.01168  -0.1116   0.8121   0.3180
   0.750   0.5066   0.02122   0.01183  -0.1115   0.8062   0.3286
   1.000   0.5347   0.02120   0.01195  -0.1115   0.8015   0.3467
   1.250   0.5581   0.02141   0.01246  -0.1114   0.7940   0.3827
   1.500   0.5866   0.02000   0.01253  -0.1106   0.7900   1.0000
   1.750   0.6091   0.02073   0.01316  -0.1103   0.7824   1.0000
   2.000   0.6367   0.02105   0.01340  -0.1101   0.7773   1.0000
   2.250   0.6604   0.02169   0.01405  -0.1098   0.7707   1.0000
   2.500   0.6856   0.02219   0.01455  -0.1096   0.7646   1.0000
   2.750   0.7152   0.02238   0.01475  -0.1095   0.7609   1.0000
   3.000   0.7337   0.02343   0.01588  -0.1091   0.7519   1.0000
   3.250   0.7628   0.02365   0.01619  -0.1089   0.7479   1.0000
   3.500   0.7811   0.02478   0.01744  -0.1085   0.7393   1.0000
   3.750   0.8111   0.02480   0.01754  -0.1081   0.7343   1.0000
   4.000   0.8310   0.02558   0.01846  -0.1073   0.7243   1.0000
   4.250   0.8605   0.02477   0.01778  -0.1054   0.7114   1.0000
   4.500   0.8952   0.02172   0.01471  -0.1011   0.6853   1.0000
   4.750   0.9241   0.01943   0.01238  -0.0972   0.6549   1.0000
   5.000   0.9489   0.01740   0.01027  -0.0930   0.6093   1.0000
   5.250   0.9588   0.01654   0.00881  -0.0872   0.4494   1.0000
   5.750   0.9500   0.02259   0.01221  -0.0782   0.0650   1.0000
   6.000   0.9639   0.02392   0.01372  -0.0760   0.0576   1.0000
   6.250   0.9750   0.02538   0.01531  -0.0734   0.0542   1.0000
   6.500   0.9872   0.02667   0.01673  -0.0710   0.0503   1.0000
   6.750   0.9967   0.02818   0.01824  -0.0684   0.0465   1.0000
   7.000   1.0074   0.03004   0.02005  -0.0658   0.0449   1.0000
   7.250   1.0352   0.03246   0.02231  -0.0651   0.0441   1.0000
   7.500   1.0753   0.03502   0.02483  -0.0658   0.0442   1.0000
   7.750   1.1082   0.03685   0.02689  -0.0655   0.0452   1.0000
   8.000   1.1414   0.03915   0.02953  -0.0649   0.0472   1.0000
   8.250   1.1682   0.04202   0.03273  -0.0640   0.0473   1.0000
   8.500   1.1913   0.04539   0.03663  -0.0623   0.0500   1.0000
   8.750   1.2256   0.05050   0.04190  -0.0623   0.0569   1.0000
  13.750   0.9494   0.17525   0.17082  -0.0853   0.1274   1.0000
  14.000   0.9614   0.17837   0.17396  -0.0845   0.1204   1.0000
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