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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.53 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe274-il-1000000-n5.txt
Download as CSV file: xf-goe274-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 274 (DAIMLER V) 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  -0.2785   0.08971   0.08805  -0.0465   0.9885   0.0089
  -8.500  -0.2656   0.08606   0.08440  -0.0502   0.9855   0.0092
  -8.000  -0.2512   0.07658   0.07491  -0.0591   0.9722   0.0106
  -7.750  -0.2355   0.07382   0.07214  -0.0626   0.9657   0.0107
  -7.500  -0.2187   0.07083   0.06914  -0.0666   0.9598   0.0109
  -7.250  -0.2016   0.06761   0.06589  -0.0707   0.9525   0.0112
  -7.000  -0.1828   0.06402   0.06226  -0.0754   0.9454   0.0116
  -6.750  -0.1599   0.05547   0.05360  -0.0865   0.9364   0.0131
  -6.500  -0.1372   0.05291   0.05099  -0.0897   0.9296   0.0133
  -6.250  -0.1137   0.05040   0.04842  -0.0925   0.9210   0.0135
  -6.000  -0.0889   0.04768   0.04562  -0.0956   0.9122   0.0137
  -5.750  -0.0629   0.04466   0.04250  -0.0988   0.9026   0.0141
  -5.500  -0.0353   0.04119   0.03889  -0.1023   0.8913   0.0148
  -5.250   0.0004   0.03356   0.03090  -0.1085   0.8803   0.0164
  -5.000   0.0264   0.03193   0.02914  -0.1096   0.8661   0.0165
  -4.750   0.0527   0.03040   0.02747  -0.1105   0.8493   0.0168
  -4.500   0.0797   0.02875   0.02563  -0.1114   0.8307   0.0171
  -4.250   0.1074   0.02706   0.02375  -0.1123   0.8113   0.0176
  -4.000   0.1364   0.02486   0.02129  -0.1132   0.7882   0.0183
  -3.750   0.1663   0.02236   0.01844  -0.1141   0.7608   0.0188
  -3.500   0.1975   0.01924   0.01484  -0.1148   0.7278   0.0194
  -3.250   0.2270   0.01700   0.01213  -0.1154   0.6891   0.0202
  -3.000   0.2538   0.01642   0.01122  -0.1155   0.6343   0.0204
  -2.750   0.2800   0.01610   0.01054  -0.1155   0.5666   0.0206
  -2.500   0.3074   0.01567   0.00983  -0.1157   0.5260   0.0209
  -2.250   0.3359   0.01504   0.00899  -0.1160   0.5028   0.0211
  -2.000   0.3646   0.01440   0.00816  -0.1162   0.4843   0.0214
  -1.750   0.3935   0.01376   0.00732  -0.1165   0.4683   0.0216
  -1.500   0.4223   0.01315   0.00654  -0.1167   0.4534   0.0217
  -1.250   0.4509   0.01272   0.00597  -0.1169   0.4389   0.0221
  -1.000   0.4796   0.01220   0.00530  -0.1170   0.4257   0.0223
  -0.750   0.5082   0.01172   0.00468  -0.1171   0.4133   0.0225
  -0.500   0.5368   0.01133   0.00420  -0.1173   0.4032   0.0228
  -0.250   0.5652   0.01105   0.00384  -0.1174   0.3931   0.0233
   0.000   0.5933   0.01090   0.00361  -0.1175   0.3802   0.0238
   0.250   0.6213   0.01083   0.00345  -0.1176   0.3651   0.0241
   0.500   0.6491   0.01079   0.00333  -0.1176   0.3487   0.0243
   0.750   0.6772   0.01075   0.00323  -0.1177   0.3367   0.0245
   1.000   0.7057   0.01054   0.00298  -0.1179   0.3281   0.0248
   1.250   0.7340   0.01043   0.00282  -0.1181   0.3183   0.0253
   1.500   0.7621   0.01040   0.00278  -0.1183   0.3090   0.0260
   1.750   0.7902   0.01042   0.00276  -0.1184   0.2995   0.0264
   2.000   0.8180   0.01046   0.00274  -0.1184   0.2886   0.0267
   2.250   0.8458   0.01051   0.00275  -0.1185   0.2775   0.0273
   2.500   0.8734   0.01059   0.00279  -0.1185   0.2649   0.0281
   2.750   0.9007   0.01073   0.00286  -0.1185   0.2497   0.0290
   3.000   0.9275   0.01091   0.00295  -0.1184   0.2325   0.0298
   3.250   0.9543   0.01111   0.00307  -0.1183   0.2152   0.0304
   3.500   0.9809   0.01131   0.00321  -0.1182   0.2002   0.0308
   3.750   1.0078   0.01149   0.00332  -0.1181   0.1891   0.0329
   4.000   1.0348   0.01163   0.00345  -0.1180   0.1827   0.0354
   4.250   1.0617   0.01179   0.00360  -0.1179   0.1766   0.0387
   4.750   1.1103   0.01064   0.00416  -0.1171   0.1645   1.0000
   5.250   1.1636   0.01106   0.00453  -0.1169   0.1547   1.0000
   5.500   1.1899   0.01128   0.00472  -0.1167   0.1493   1.0000
   5.750   1.2159   0.01154   0.00494  -0.1165   0.1424   1.0000
   6.000   1.2421   0.01177   0.00515  -0.1163   0.1353   1.0000
   6.250   1.2675   0.01208   0.00539  -0.1160   0.1246   1.0000
   6.750   1.3125   0.01333   0.00632  -0.1146   0.0741   1.0000
   7.000   1.3372   0.01366   0.00665  -0.1142   0.0677   1.0000
   7.250   1.3541   0.01489   0.00761  -0.1125   0.0193   1.0000
   7.500   1.3776   0.01531   0.00803  -0.1119   0.0148   1.0000
   7.750   1.4013   0.01569   0.00844  -0.1113   0.0132   1.0000
   8.000   1.4243   0.01612   0.00888  -0.1106   0.0117   1.0000
   8.250   1.4471   0.01655   0.00934  -0.1099   0.0107   1.0000
   8.500   1.4699   0.01694   0.00976  -0.1091   0.0101   1.0000
   8.750   1.4922   0.01737   0.01023  -0.1083   0.0094   1.0000
   9.000   1.5136   0.01784   0.01072  -0.1074   0.0087   1.0000
   9.250   1.5337   0.01842   0.01133  -0.1063   0.0079   1.0000
   9.500   1.5544   0.01889   0.01185  -0.1053   0.0076   1.0000
   9.750   1.5745   0.01939   0.01240  -0.1041   0.0072   1.0000
  10.000   1.5935   0.01992   0.01297  -0.1028   0.0069   1.0000
  10.250   1.6116   0.02047   0.01357  -0.1014   0.0066   1.0000
  10.500   1.6285   0.02106   0.01420  -0.0997   0.0063   1.0000
  10.750   1.6438   0.02171   0.01489  -0.0978   0.0060   1.0000
  11.000   1.6553   0.02248   0.01574  -0.0952   0.0056   1.0000
  11.250   1.6659   0.02326   0.01658  -0.0925   0.0054   1.0000
  11.500   1.6778   0.02398   0.01737  -0.0902   0.0053   1.0000
  11.750   1.6891   0.02478   0.01823  -0.0879   0.0051   1.0000
  12.000   1.6994   0.02567   0.01920  -0.0855   0.0049   1.0000
  12.250   1.7088   0.02665   0.02026  -0.0831   0.0048   1.0000
  12.500   1.7174   0.02771   0.02139  -0.0808   0.0046   1.0000
  12.750   1.7254   0.02886   0.02262  -0.0785   0.0045   1.0000
  13.000   1.7323   0.03013   0.02396  -0.0763   0.0044   1.0000
  13.250   1.7383   0.03152   0.02543  -0.0741   0.0042   1.0000
  13.500   1.7429   0.03309   0.02709  -0.0720   0.0041   1.0000
  13.750   1.7453   0.03491   0.02899  -0.0700   0.0040   1.0000
  14.000   1.7454   0.03707   0.03126  -0.0680   0.0039   1.0000
  14.250   1.7421   0.03968   0.03399  -0.0662   0.0038   1.0000
  14.500   1.7354   0.04284   0.03727  -0.0647   0.0037   1.0000
  14.750   1.7325   0.04581   0.04036  -0.0638   0.0037   1.0000
  15.000   1.7279   0.04919   0.04387  -0.0632   0.0037   1.0000
  15.250   1.7209   0.05308   0.04788  -0.0631   0.0036   1.0000
  15.500   1.7116   0.05761   0.05255  -0.0636   0.0036   1.0000
  15.750   1.7011   0.06264   0.05772  -0.0646   0.0036   1.0000
  16.000   1.6868   0.06855   0.06378  -0.0663   0.0036   1.0000
  16.250   1.6701   0.07500   0.07038  -0.0683   0.0036   1.0000
  16.500   1.6515   0.08184   0.07737  -0.0704   0.0035   1.0000
  16.750   1.6293   0.08925   0.08492  -0.0728   0.0035   1.0000
  17.000   1.6074   0.09662   0.09243  -0.0752   0.0035   1.0000
  17.250   1.5842   0.10433   0.10027  -0.0779   0.0035   1.0000
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