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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 500,000
Max Cl/Cd: 132.84 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe495-il-500000.txt
Download as CSV file: xf-goe495-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3507   0.09921   0.09698  -0.0338   1.0000   0.0183
  -8.500  -0.3542   0.09695   0.09476  -0.0327   1.0000   0.0184
  -8.250  -0.3627   0.09338   0.09124  -0.0303   1.0000   0.0190
  -8.000  -0.3639   0.09232   0.09021  -0.0273   1.0000   0.0194
  -7.750  -0.3472   0.08906   0.08695  -0.0308   0.9980   0.0200
  -7.500  -0.3279   0.08519   0.08307  -0.0360   0.9950   0.0207
  -7.250  -0.3101   0.08121   0.07910  -0.0414   0.9901   0.0214
  -7.000  -0.2837   0.07601   0.07389  -0.0500   0.9856   0.0228
  -6.750  -0.2473   0.06944   0.06729  -0.0645   0.9793   0.0245
  -6.500  -0.2148   0.06320   0.06102  -0.0752   0.9746   0.0247
  -6.250  -0.1754   0.05546   0.05321  -0.0886   0.9718   0.0247
  -6.000  -0.1210   0.02387   0.02044  -0.1264   0.9621   0.0197
  -5.750  -0.0866   0.02495   0.02169  -0.1276   0.9604   0.0214
  -5.500  -0.0465   0.01917   0.01510  -0.1333   0.9581   0.0224
  -5.250  -0.0154   0.01698   0.01248  -0.1346   0.9525   0.0237
  -5.000   0.0172   0.01560   0.01073  -0.1359   0.9479   0.0250
  -4.750   0.0496   0.01360   0.00852  -0.1376   0.9445   0.0278
  -4.500   0.0790   0.01288   0.00769  -0.1380   0.9389   0.0299
  -4.250   0.1090   0.01212   0.00676  -0.1384   0.9332   0.0319
  -4.000   0.1412   0.01192   0.00643  -0.1390   0.9292   0.0335
  -3.750   0.1674   0.01036   0.00472  -0.1389   0.9216   0.0368
  -3.500   0.1973   0.00985   0.00414  -0.1392   0.9162   0.0392
  -3.250   0.2250   0.00950   0.00374  -0.1391   0.9092   0.0418
  -3.000   0.2537   0.00918   0.00333  -0.1391   0.9029   0.0437
  -2.750   0.2817   0.00882   0.00290  -0.1390   0.8962   0.0454
  -2.500   0.3098   0.00842   0.00245  -0.1389   0.8895   0.0500
  -2.250   0.3379   0.00823   0.00221  -0.1389   0.8830   0.0545
  -2.000   0.3657   0.00801   0.00197  -0.1387   0.8760   0.0636
  -1.750   0.3936   0.00766   0.00185  -0.1387   0.8696   0.1335
  -1.500   0.4209   0.00752   0.00179  -0.1385   0.8624   0.1726
  -1.250   0.4488   0.00742   0.00174  -0.1384   0.8560   0.2069
  -1.000   0.4759   0.00729   0.00172  -0.1382   0.8484   0.2487
  -0.750   0.5035   0.00719   0.00171  -0.1381   0.8419   0.3013
  -0.500   0.5304   0.00708   0.00174  -0.1378   0.8341   0.3552
  -0.250   0.5577   0.00698   0.00176  -0.1376   0.8270   0.4165
   0.000   0.5841   0.00682   0.00180  -0.1372   0.8176   0.4976
   0.250   0.6096   0.00660   0.00185  -0.1366   0.8067   0.6034
   0.500   0.6353   0.00582   0.00184  -0.1358   0.7967   1.0000
   0.750   0.6623   0.00589   0.00182  -0.1354   0.7867   1.0000
   1.000   0.6890   0.00595   0.00183  -0.1350   0.7755   1.0000
   1.250   0.7159   0.00602   0.00184  -0.1346   0.7648   1.0000
   1.500   0.7429   0.00610   0.00188  -0.1343   0.7548   1.0000
   1.750   0.7696   0.00617   0.00191  -0.1339   0.7436   1.0000
   2.000   0.7961   0.00625   0.00195  -0.1334   0.7305   1.0000
   2.250   0.8225   0.00634   0.00200  -0.1330   0.7163   1.0000
   2.500   0.8487   0.00645   0.00208  -0.1325   0.7012   1.0000
   2.750   0.8741   0.00658   0.00214  -0.1318   0.6796   1.0000
   3.000   0.8985   0.00677   0.00221  -0.1309   0.6501   1.0000
   3.250   0.9230   0.00699   0.00232  -0.1301   0.6227   1.0000
   3.500   0.9473   0.00725   0.00247  -0.1292   0.5948   1.0000
   3.750   0.9715   0.00751   0.00264  -0.1284   0.5673   1.0000
   4.000   0.9953   0.00782   0.00283  -0.1276   0.5354   1.0000
   4.250   1.0188   0.00816   0.00305  -0.1267   0.5021   1.0000
   4.500   1.0408   0.00861   0.00332  -0.1255   0.4547   1.0000
   4.750   1.0613   0.00922   0.00364  -0.1242   0.3884   1.0000
   5.000   1.0789   0.01016   0.00413  -0.1225   0.3022   1.0000
   5.250   1.0947   0.01137   0.00477  -0.1207   0.1963   1.0000
   5.500   1.1135   0.01229   0.00537  -0.1193   0.1395   1.0000
   5.750   1.1300   0.01345   0.00609  -0.1175   0.0652   1.0000
   6.000   1.1510   0.01414   0.00669  -0.1163   0.0478   1.0000
   6.250   1.1720   0.01482   0.00736  -0.1151   0.0402   1.0000
   6.500   1.1941   0.01535   0.00795  -0.1141   0.0361   1.0000
   7.000   1.2338   0.01683   0.00954  -0.1113   0.0280   1.0000
   7.250   1.2540   0.01748   0.01023  -0.1100   0.0252   1.0000
   7.500   1.2651   0.01909   0.01191  -0.1073   0.0222   1.0000
   7.750   1.2867   0.01955   0.01244  -0.1062   0.0210   1.0000
   8.000   1.3066   0.02016   0.01311  -0.1049   0.0193   1.0000
   8.250   1.3258   0.02080   0.01379  -0.1036   0.0179   1.0000
   8.500   1.3385   0.02214   0.01518  -0.1012   0.0166   1.0000
   8.750   1.3507   0.02378   0.01694  -0.0988   0.0157   1.0000
   9.000   1.3674   0.02472   0.01799  -0.0970   0.0151   1.0000
   9.250   1.3825   0.02586   0.01924  -0.0951   0.0145   1.0000
   9.500   1.3971   0.02697   0.02044  -0.0931   0.0138   1.0000
   9.750   1.4107   0.02785   0.02141  -0.0910   0.0130   1.0000
  10.000   1.4230   0.02878   0.02239  -0.0889   0.0124   1.0000
  10.250   1.4335   0.03115   0.02488  -0.0869   0.0117   1.0000
  10.500   1.4455   0.03397   0.02796  -0.0850   0.0113   1.0000
  10.750   1.4548   0.03558   0.02977  -0.0826   0.0111   1.0000
  11.000   1.4621   0.03755   0.03195  -0.0801   0.0108   1.0000
  11.250   1.4665   0.03988   0.03452  -0.0775   0.0106   1.0000
  11.500   1.4672   0.04256   0.03746  -0.0747   0.0104   1.0000
  11.750   1.4640   0.04557   0.04074  -0.0718   0.0102   1.0000
  12.000   1.4568   0.04895   0.04440  -0.0691   0.0101   1.0000
  12.250   1.4456   0.05280   0.04853  -0.0666   0.0100   1.0000
  12.500   1.4306   0.05721   0.05324  -0.0646   0.0100   1.0000
  12.750   1.4124   0.06216   0.05846  -0.0632   0.0100   1.0000
  13.000   1.3913   0.06777   0.06433  -0.0628   0.0100   1.0000
  13.250   1.3685   0.07397   0.07076  -0.0634   0.0101   1.0000
  13.500   1.3447   0.08082   0.07785  -0.0651   0.0101   1.0000
  13.750   1.3202   0.08839   0.08562  -0.0681   0.0102   1.0000
  14.000   1.2959   0.09674   0.09417  -0.0723   0.0103   1.0000
  14.250   1.2721   0.10589   0.10350  -0.0777   0.0104   1.0000
  14.500   1.2482   0.11616   0.11393  -0.0843   0.0106   1.0000
  14.750   1.2241   0.12783   0.12574  -0.0923   0.0107   1.0000
  15.000   1.1974   0.14193   0.13997  -0.1019   0.0110   1.0000
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