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UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)
Reynolds number: 500,000
Max Cl/Cd: 93.28 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gu255118-il-500000-n5.txt
Download as CSV file: xf-gu255118-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF GLASGOW GU25-5(11)8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.1498   0.08947   0.08460  -0.1618   0.6184   0.0168
 -12.000   0.1490   0.08596   0.08110  -0.1630   0.6177   0.0169
 -11.750   0.1472   0.08238   0.07753  -0.1642   0.6168   0.0171
 -11.500   0.1415   0.07825   0.07343  -0.1656   0.6161   0.0177
 -11.250  -0.0592   0.04254   0.03769  -0.1822   0.6168   0.0177
 -11.000  -0.1150   0.03692   0.03183  -0.1809   0.6160   0.0177
 -10.750  -0.1451   0.03407   0.02879  -0.1766   0.6151   0.0178
 -10.500  -0.1720   0.03169   0.02619  -0.1708   0.6142   0.0179
 -10.250  -0.1919   0.02986   0.02412  -0.1649   0.6134   0.0180
 -10.000  -0.1994   0.02801   0.02199  -0.1606   0.6125   0.0184
  -9.500  -0.1932   0.02509   0.01859  -0.1545   0.6109   0.0188
  -9.250  -0.1831   0.02397   0.01726  -0.1522   0.6102   0.0191
  -9.000  -0.1691   0.02317   0.01628  -0.1503   0.6094   0.0193
  -8.750  -0.1556   0.02208   0.01507  -0.1486   0.6087   0.0196
  -8.500  -0.1381   0.02143   0.01434  -0.1473   0.6079   0.0198
  -8.250  -0.1191   0.02092   0.01378  -0.1462   0.6071   0.0201
  -8.000  -0.0997   0.02040   0.01318  -0.1451   0.6063   0.0204
  -7.750  -0.0799   0.01983   0.01253  -0.1441   0.6056   0.0206
  -7.500  -0.0594   0.01934   0.01195  -0.1431   0.6048   0.0210
  -7.250  -0.0387   0.01879   0.01131  -0.1422   0.6041   0.0212
  -7.000  -0.0173   0.01830   0.01074  -0.1413   0.6034   0.0216
  -6.750   0.0042   0.01780   0.01014  -0.1405   0.6026   0.0220
  -6.500   0.0262   0.01736   0.00961  -0.1397   0.6018   0.0224
  -6.250   0.0484   0.01693   0.00911  -0.1389   0.6011   0.0228
  -6.000   0.0709   0.01656   0.00866  -0.1382   0.6003   0.0231
  -5.750   0.0939   0.01626   0.00828  -0.1375   0.5996   0.0235
  -5.500   0.1160   0.01587   0.00783  -0.1367   0.5990   0.0240
  -5.250   0.1378   0.01548   0.00743  -0.1359   0.5984   0.0245
  -5.000   0.1607   0.01522   0.00714  -0.1352   0.5978   0.0250
  -4.750   0.1839   0.01499   0.00688  -0.1347   0.5972   0.0256
  -4.500   0.2071   0.01476   0.00661  -0.1340   0.5966   0.0261
  -4.250   0.2301   0.01453   0.00636  -0.1334   0.5961   0.0266
  -4.000   0.2530   0.01433   0.00614  -0.1327   0.5957   0.0273
  -3.750   0.2760   0.01414   0.00593  -0.1320   0.5953   0.0279
  -3.500   0.2993   0.01399   0.00575  -0.1313   0.5948   0.0285
  -3.250   0.3218   0.01379   0.00555  -0.1306   0.5944   0.0293
  -3.000   0.3445   0.01360   0.00537  -0.1298   0.5939   0.0304
  -2.750   0.3680   0.01349   0.00525  -0.1293   0.5934   0.0315
  -2.500   0.3917   0.01338   0.00514  -0.1287   0.5929   0.0325
  -2.250   0.4156   0.01330   0.00504  -0.1282   0.5924   0.0337
  -2.000   0.4396   0.01323   0.00495  -0.1277   0.5919   0.0348
  -1.750   0.4633   0.01314   0.00487  -0.1272   0.5914   0.0369
  -1.500   0.4872   0.01308   0.00482  -0.1267   0.5909   0.0400
  -1.250   0.5110   0.01302   0.00478  -0.1262   0.5904   0.0464
  -1.000   0.5336   0.01289   0.00476  -0.1255   0.5900   0.0737
  -0.750   0.5551   0.01270   0.00475  -0.1246   0.5895   0.1289
  -0.500   0.5752   0.01243   0.00475  -0.1235   0.5890   0.2167
  -0.250   0.5931   0.01206   0.00477  -0.1220   0.5885   0.3436
   0.000   0.6092   0.01170   0.00483  -0.1201   0.5881   0.4827
   0.250   0.6278   0.01154   0.00491  -0.1186   0.5876   0.5647
   0.500   0.6444   0.01135   0.00501  -0.1165   0.5871   0.6488
   0.750   0.6579   0.01111   0.00511  -0.1137   0.5866   0.7508
   1.250   0.8276   0.01131   0.00572  -0.1391   0.5858   0.9342
   1.500   0.8612   0.01147   0.00585  -0.1408   0.5854   0.9453
   2.000   0.9247   0.01180   0.00613  -0.1433   0.5846   0.9630
   2.500   0.9897   0.01213   0.00642  -0.1463   0.5839   0.9752
   2.750   1.0225   0.01230   0.00657  -0.1479   0.5835   0.9803
   3.000   1.0560   0.01247   0.00672  -0.1497   0.5831   0.9842
   3.250   1.0922   0.01263   0.00687  -0.1521   0.5828   0.9871
   3.500   1.1268   0.01281   0.00704  -0.1542   0.5824   0.9902
   3.750   1.1606   0.01300   0.00723  -0.1561   0.5820   0.9932
   4.000   1.1961   0.01318   0.00741  -0.1584   0.5816   0.9955
   4.250   1.2310   0.01337   0.00761  -0.1606   0.5812   0.9980
   4.500   1.2630   0.01354   0.00783  -0.1623   0.5807   1.0000
   4.750   1.2781   0.01374   0.00807  -0.1602   0.5802   1.0000
   5.000   1.2933   0.01395   0.00832  -0.1582   0.5797   1.0000
   5.250   1.3081   0.01417   0.00858  -0.1562   0.5792   1.0000
   5.500   1.3214   0.01441   0.00886  -0.1538   0.5785   1.0000
   5.750   1.3321   0.01463   0.00913  -0.1509   0.5774   1.0000
   6.000   1.3420   0.01484   0.00939  -0.1479   0.5762   1.0000
   6.250   1.3500   0.01504   0.00963  -0.1444   0.5752   1.0000
   6.500   1.3571   0.01524   0.00986  -0.1408   0.5742   1.0000
   6.750   1.3668   0.01544   0.01011  -0.1377   0.5732   1.0000
   7.000   1.3789   0.01565   0.01036  -0.1352   0.5723   1.0000
   7.250   1.3935   0.01586   0.01060  -0.1332   0.5713   1.0000
   7.500   1.4104   0.01604   0.01080  -0.1317   0.5704   1.0000
   7.750   1.4295   0.01621   0.01101  -0.1307   0.5695   1.0000
   8.000   1.4522   0.01631   0.01113  -0.1303   0.5685   1.0000
   8.250   1.4779   0.01639   0.01122  -0.1305   0.5674   1.0000
   8.500   1.4918   0.01667   0.01154  -0.1285   0.5660   1.0000
   8.750   1.4617   0.01780   0.01282  -0.1192   0.5631   1.0000
   9.000   1.4492   0.01890   0.01401  -0.1134   0.5602   1.0000
   9.250   1.4560   0.01949   0.01465  -0.1109   0.5576   1.0000
   9.500   1.4805   0.01937   0.01454  -0.1108   0.5551   1.0000
   9.750   1.5132   0.01894   0.01410  -0.1120   0.5526   1.0000
  10.000   1.4851   0.02121   0.01650  -0.1050   0.5490   1.0000
  10.250   1.4428   0.02474   0.02017  -0.0971   0.5429   1.0000
  10.500   1.4764   0.02404   0.01945  -0.0982   0.5390   1.0000
  11.250   1.2607   0.04566   0.04137  -0.0718   0.4896   1.0000
  11.500   1.2909   0.04514   0.04086  -0.0725   0.4856   1.0000
  12.000   1.3581   0.04345   0.03912  -0.0743   0.4691   1.0000
  12.250   1.3873   0.04285   0.03842  -0.0747   0.4545   1.0000
  12.500   1.3969   0.04388   0.03935  -0.0735   0.4354   1.0000
  12.750   1.3983   0.04563   0.04100  -0.0717   0.4170   1.0000
  13.000   1.3851   0.04864   0.04384  -0.0687   0.3908   1.0000
  13.250   1.3668   0.05220   0.04722  -0.0655   0.3624   1.0000
  13.500   1.3554   0.05531   0.05022  -0.0631   0.3401   1.0000
  13.750   1.3408   0.05878   0.05355  -0.0605   0.3147   1.0000
  14.000   1.3358   0.06149   0.05617  -0.0588   0.2961   1.0000
  14.250   1.3236   0.06489   0.05943  -0.0566   0.2709   1.0000
  14.500   1.3167   0.06787   0.06229  -0.0549   0.2491   1.0000
  14.750   1.3125   0.07063   0.06496  -0.0535   0.2289   1.0000
  15.000   1.3053   0.07375   0.06797  -0.0519   0.2061   1.0000
  15.250   1.3011   0.07660   0.07070  -0.0506   0.1846   1.0000
  15.500   1.2981   0.07936   0.07336  -0.0495   0.1653   1.0000
  15.750   1.2942   0.08225   0.07615  -0.0484   0.1455   1.0000
  16.000   1.2883   0.08539   0.07913  -0.0472   0.1208   1.0000
  16.250   1.2872   0.08810   0.08177  -0.0464   0.1051   1.0000
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