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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 1,000,000
Max Cl/Cd: 158.88 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe495-il-1000000.txt
Download as CSV file: xf-goe495-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 495 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3539   0.10202   0.10039  -0.0303   1.0000   0.0109
  -9.000  -0.3529   0.09983   0.09823  -0.0298   1.0000   0.0112
  -8.750  -0.3537   0.09772   0.09614  -0.0290   1.0000   0.0119
  -8.500  -0.3443   0.09392   0.09235  -0.0320   0.9992   0.0129
  -8.250  -0.3281   0.08841   0.08684  -0.0393   0.9970   0.0136
  -8.000  -0.3110   0.08393   0.08236  -0.0447   0.9948   0.0136
  -7.750  -0.2975   0.01669   0.01343  -0.1306   0.9746   0.0104
  -7.500  -0.2631   0.01533   0.01188  -0.1331   0.9732   0.0110
  -7.250  -0.2290   0.01460   0.01104  -0.1349   0.9717   0.0115
  -7.000  -0.1993   0.01375   0.01003  -0.1357   0.9676   0.0121
  -6.750  -0.1695   0.01288   0.00898  -0.1365   0.9626   0.0128
  -6.500  -0.1372   0.01219   0.00814  -0.1376   0.9586   0.0135
  -6.250  -0.1093   0.01079   0.00650  -0.1381   0.9511   0.0146
  -6.000  -0.0788   0.01071   0.00642  -0.1386   0.9445   0.0155
  -5.750  -0.0505   0.01056   0.00622  -0.1386   0.9363   0.0166
  -5.250   0.0066   0.01016   0.00564  -0.1387   0.9199   0.0183
  -5.000   0.0338   0.00914   0.00448  -0.1388   0.9113   0.0203
  -4.750   0.0616   0.00900   0.00429  -0.1387   0.9026   0.0217
  -4.500   0.0892   0.00891   0.00415  -0.1386   0.8942   0.0234
  -4.250   0.1171   0.00887   0.00403  -0.1384   0.8863   0.0245
  -4.000   0.1440   0.00808   0.00311  -0.1383   0.8781   0.0265
  -3.750   0.1715   0.00781   0.00278  -0.1382   0.8709   0.0285
  -3.500   0.1990   0.00764   0.00257  -0.1381   0.8635   0.0305
  -3.250   0.2266   0.00747   0.00232  -0.1379   0.8570   0.0319
  -3.000   0.2543   0.00732   0.00212  -0.1378   0.8502   0.0330
  -2.500   0.3097   0.00686   0.00152  -0.1375   0.8375   0.0368
  -2.250   0.3374   0.00672   0.00133  -0.1374   0.8314   0.0398
  -2.000   0.3651   0.00661   0.00119  -0.1372   0.8253   0.0427
  -1.750   0.3928   0.00653   0.00107  -0.1371   0.8190   0.0461
  -1.500   0.4204   0.00627   0.00097  -0.1370   0.8131   0.0990
  -1.250   0.4480   0.00613   0.00094  -0.1369   0.8066   0.1411
  -1.000   0.4754   0.00608   0.00092  -0.1368   0.8000   0.1677
  -0.750   0.5027   0.00596   0.00090  -0.1366   0.7911   0.2038
   0.000   0.5841   0.00573   0.00091  -0.1359   0.7613   0.3339
   0.250   0.6111   0.00565   0.00094  -0.1357   0.7508   0.3908
   0.500   0.6381   0.00560   0.00097  -0.1355   0.7407   0.4409
   0.750   0.6650   0.00550   0.00103  -0.1352   0.7302   0.5123
   1.000   0.6914   0.00532   0.00111  -0.1350   0.7188   0.6226
   1.250   0.7168   0.00464   0.00117  -0.1343   0.7068   1.0000
   1.500   0.7434   0.00475   0.00120  -0.1339   0.6902   1.0000
   1.750   0.7697   0.00487   0.00125  -0.1335   0.6727   1.0000
   2.000   0.7960   0.00501   0.00130  -0.1330   0.6534   1.0000
   2.250   0.8213   0.00521   0.00138  -0.1324   0.6255   1.0000
   2.500   0.8463   0.00545   0.00148  -0.1318   0.5941   1.0000
   2.750   0.8716   0.00567   0.00159  -0.1312   0.5688   1.0000
   3.000   0.8968   0.00591   0.00172  -0.1306   0.5405   1.0000
   3.250   0.9219   0.00617   0.00185  -0.1300   0.5112   1.0000
   3.500   0.9473   0.00641   0.00201  -0.1295   0.4854   1.0000
   3.750   0.9716   0.00674   0.00218  -0.1288   0.4464   1.0000
   4.000   0.9937   0.00728   0.00243  -0.1278   0.3833   1.0000
   4.250   1.0151   0.00793   0.00276  -0.1267   0.3154   1.0000
   4.500   1.0350   0.00875   0.00318  -0.1254   0.2331   1.0000
   4.750   1.0549   0.00958   0.00364  -0.1242   0.1624   1.0000
   5.000   1.0780   0.01007   0.00398  -0.1234   0.1302   1.0000
   5.250   1.0981   0.01087   0.00445  -0.1221   0.0700   1.0000
   5.500   1.1197   0.01152   0.00491  -0.1211   0.0412   1.0000
   5.750   1.1440   0.01186   0.00526  -0.1204   0.0369   1.0000
   6.000   1.1670   0.01233   0.00573  -0.1195   0.0311   1.0000
   6.250   1.1916   0.01260   0.00603  -0.1189   0.0292   1.0000
   6.500   1.2154   0.01296   0.00639  -0.1182   0.0261   1.0000
   6.750   1.2371   0.01354   0.00701  -0.1171   0.0220   1.0000
   7.000   1.2613   0.01381   0.00729  -0.1165   0.0202   1.0000
   7.250   1.2841   0.01423   0.00769  -0.1157   0.0176   1.0000
   7.500   1.3053   0.01482   0.00833  -0.1145   0.0155   1.0000
   7.750   1.3280   0.01522   0.00875  -0.1137   0.0143   1.0000
   8.000   1.3498   0.01569   0.00925  -0.1127   0.0132   1.0000
   8.250   1.3673   0.01661   0.01023  -0.1110   0.0117   1.0000
   8.500   1.3870   0.01724   0.01093  -0.1096   0.0111   1.0000
   8.750   1.4078   0.01774   0.01148  -0.1085   0.0105   1.0000
   9.000   1.4278   0.01828   0.01206  -0.1073   0.0099   1.0000
   9.250   1.4472   0.01885   0.01267  -0.1060   0.0093   1.0000
   9.500   1.4638   0.01964   0.01351  -0.1042   0.0088   1.0000
   9.750   1.4689   0.02144   0.01548  -0.1006   0.0081   1.0000
  10.000   1.4839   0.02210   0.01621  -0.0986   0.0079   1.0000
  10.250   1.4974   0.02282   0.01701  -0.0963   0.0077   1.0000
  10.500   1.5090   0.02368   0.01796  -0.0938   0.0074   1.0000
  10.750   1.5195   0.02465   0.01902  -0.0912   0.0072   1.0000
  11.000   1.5297   0.02565   0.02011  -0.0888   0.0069   1.0000
  11.250   1.5394   0.02670   0.02127  -0.0864   0.0067   1.0000
  11.500   1.5482   0.02786   0.02251  -0.0840   0.0065   1.0000
  11.750   1.5565   0.02906   0.02381  -0.0817   0.0063   1.0000
  12.000   1.5640   0.03035   0.02518  -0.0795   0.0062   1.0000
  12.250   1.5698   0.03183   0.02675  -0.0772   0.0060   1.0000
  12.500   1.5703   0.03394   0.02899  -0.0747   0.0058   1.0000
  12.750   1.5553   0.03807   0.03341  -0.0712   0.0055   1.0000
  13.000   1.5565   0.04030   0.03578  -0.0694   0.0054   1.0000
  13.250   1.5598   0.04229   0.03791  -0.0679   0.0053   1.0000
  13.500   1.5621   0.04447   0.04022  -0.0666   0.0052   1.0000
  13.750   1.5604   0.04725   0.04315  -0.0654   0.0052   1.0000
  14.000   1.5570   0.05035   0.04642  -0.0644   0.0051   1.0000
  14.250   1.5512   0.05390   0.05014  -0.0638   0.0050   1.0000
  14.500   1.5439   0.05782   0.05422  -0.0635   0.0049   1.0000
  14.750   1.5346   0.06224   0.05882  -0.0638   0.0049   1.0000
  15.000   1.5233   0.06722   0.06397  -0.0646   0.0048   1.0000
  15.250   1.5100   0.07286   0.06979  -0.0660   0.0048   1.0000
  15.500   1.4953   0.07912   0.07623  -0.0682   0.0048   1.0000
  15.750   1.4783   0.08624   0.08353  -0.0711   0.0048   1.0000
  16.000   1.4596   0.09414   0.09162  -0.0749   0.0048   1.0000
  16.250   1.4389   0.10301   0.10067  -0.0796   0.0047   1.0000
  16.500   1.4167   0.11277   0.11061  -0.0852   0.0048   1.0000
  16.750   1.3914   0.12400   0.12203  -0.0921   0.0048   1.0000
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