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UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)
Reynolds number: 200,000
Max Cl/Cd: 38.32 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gu255118-il-200000-n5.txt
Download as CSV file: xf-gu255118-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.1565   0.10101   0.09486  -0.1581   0.6551   0.0409
 -12.000   0.1509   0.09724   0.09113  -0.1602   0.6541   0.0412
 -11.750   0.1509   0.09383   0.08774  -0.1616   0.6531   0.0412
 -11.250   0.1431   0.08230   0.07621  -0.1633   0.6512   0.0287
 -11.000   0.1457   0.07958   0.07351  -0.1640   0.6502   0.0285
 -10.750   0.1428   0.07599   0.06995  -0.1651   0.6493   0.0285
 -10.500   0.1419   0.07294   0.06692  -0.1660   0.6482   0.0283
 -10.250   0.1350   0.06892   0.06294  -0.1674   0.6474   0.0281
 -10.000   0.1018   0.05943   0.05350  -0.1724   0.6466   0.0281
  -9.750   0.0733   0.05306   0.04708  -0.1761   0.6457   0.0277
  -9.500   0.0372   0.04844   0.04235  -0.1759   0.6448   0.0275
  -9.250   0.0064   0.04538   0.03914  -0.1721   0.6440   0.0275
  -9.000  -0.0206   0.04304   0.03660  -0.1669   0.6432   0.0276
  -8.750  -0.0389   0.04036   0.03362  -0.1626   0.6424   0.0279
  -8.500  -0.0481   0.03804   0.03102  -0.1588   0.6415   0.0280
  -8.250  -0.0524   0.03587   0.02857  -0.1551   0.6406   0.0282
  -8.000  -0.0522   0.03391   0.02629  -0.1518   0.6396   0.0283
  -7.750  -0.0465   0.03231   0.02440  -0.1490   0.6386   0.0285
  -7.500  -0.0384   0.03089   0.02265  -0.1463   0.6376   0.0288
  -7.250  -0.0254   0.02949   0.02109  -0.1446   0.6367   0.0290
  -7.000  -0.0096   0.02846   0.01993  -0.1431   0.6357   0.0294
  -6.750   0.0074   0.02755   0.01888  -0.1417   0.6347   0.0298
  -6.500   0.0258   0.02682   0.01803  -0.1405   0.6336   0.0304
  -6.250   0.0452   0.02617   0.01727  -0.1395   0.6327   0.0311
  -6.000   0.0653   0.02550   0.01647  -0.1385   0.6318   0.0320
  -5.750   0.0861   0.02480   0.01559  -0.1375   0.6310   0.0328
  -5.500   0.1078   0.02412   0.01475  -0.1367   0.6303   0.0333
  -5.250   0.1303   0.02352   0.01401  -0.1360   0.6296   0.0338
  -5.000   0.1532   0.02301   0.01338  -0.1353   0.6290   0.0343
  -4.750   0.1758   0.02243   0.01274  -0.1347   0.6284   0.0350
  -4.500   0.1980   0.02195   0.01225  -0.1340   0.6278   0.0357
  -4.250   0.2204   0.02162   0.01190  -0.1334   0.6272   0.0368
  -4.000   0.2430   0.02138   0.01163  -0.1328   0.6267   0.0384
  -3.750   0.2604   0.02122   0.01147  -0.1311   0.6259   0.0396
  -3.500   0.2773   0.02110   0.01134  -0.1294   0.6251   0.0405
  -3.250   0.2937   0.02101   0.01125  -0.1275   0.6243   0.0413
  -3.000   0.3086   0.02089   0.01116  -0.1255   0.6234   0.0426
  -2.750   0.3243   0.02088   0.01117  -0.1235   0.6225   0.0439
  -2.500   0.3400   0.02092   0.01121  -0.1216   0.6216   0.0457
  -2.250   0.3557   0.02102   0.01129  -0.1197   0.6208   0.0484
  -2.000   0.3706   0.02109   0.01139  -0.1176   0.6199   0.0516
  -1.750   0.3859   0.02118   0.01149  -0.1156   0.6189   0.0559
  -1.500   0.4015   0.02123   0.01157  -0.1136   0.6178   0.0633
  -1.250   0.4168   0.02126   0.01167  -0.1117   0.6169   0.0821
  -1.000   0.4293   0.02119   0.01184  -0.1093   0.6161   0.1414
  -0.750   0.4386   0.02094   0.01204  -0.1064   0.6153   0.2670
  -0.500   0.4446   0.02062   0.01232  -0.1029   0.6146   0.4320
  -0.250   0.4530   0.02053   0.01263  -0.0995   0.6138   0.5539
   0.000   0.4634   0.02049   0.01294  -0.0963   0.6132   0.6550
   0.500   0.6949   0.02091   0.01390  -0.1324   0.6133   0.9647
   0.750   0.7311   0.02127   0.01417  -0.1348   0.6129   0.9760
   1.000   0.7687   0.02160   0.01443  -0.1375   0.6125   0.9849
   1.250   0.8084   0.02193   0.01467  -0.1407   0.6121   0.9919
   1.500   0.8499   0.02218   0.01484  -0.1443   0.6116   0.9975
   4.000   0.5324   0.04944   0.04255  -0.0692   0.5554   1.0000
   4.250   0.5553   0.04973   0.04279  -0.0689   0.5544   1.0000
   4.500   0.5796   0.04992   0.04293  -0.0687   0.5536   1.0000
   4.750   0.6046   0.05005   0.04300  -0.0687   0.5528   1.0000
   5.000   0.6301   0.05013   0.04305  -0.0686   0.5522   1.0000
   5.500   0.6292   0.05383   0.04676  -0.0644   0.5399   1.0000
   5.750   0.6540   0.05395   0.04684  -0.0643   0.5390   1.0000
   6.000   0.6789   0.05407   0.04694  -0.0643   0.5382   1.0000
   6.250   0.7047   0.05410   0.04694  -0.0643   0.5376   1.0000
   6.750   0.7090   0.05757   0.05044  -0.0608   0.5253   1.0000
   7.000   0.7347   0.05755   0.05041  -0.0609   0.5245   1.0000
   7.250   0.7604   0.05755   0.05040  -0.0609   0.5238   1.0000
   7.750   0.7691   0.06081   0.05371  -0.0581   0.5117   1.0000
   8.000   0.7944   0.06080   0.05371  -0.0581   0.5109   1.0000
   8.500   0.8078   0.06383   0.05679  -0.0558   0.4993   1.0000
   8.750   0.8330   0.06377   0.05674  -0.0558   0.4981   1.0000
   9.000   0.8582   0.06372   0.05671  -0.0559   0.4973   1.0000
   9.500   0.8744   0.06657   0.05964  -0.0540   0.4855   1.0000
   9.750   0.8993   0.06652   0.05961  -0.0540   0.4845   1.0000
  10.000   0.9253   0.06633   0.05946  -0.0542   0.4837   1.0000
  10.500   0.9428   0.06916   0.06238  -0.0524   0.4717   1.0000
  10.750   0.9687   0.06893   0.06218  -0.0526   0.4706   1.0000
  12.750   1.0884   0.07561   0.06933  -0.0492   0.4336   1.0000
  13.000   1.1104   0.07568   0.06946  -0.0492   0.4301   1.0000
  13.250   1.1372   0.07523   0.06908  -0.0494   0.4280   1.0000
  13.500   1.1670   0.07445   0.06837  -0.0498   0.4264   1.0000
  14.000   1.1951   0.07634   0.07039  -0.0490   0.4127   1.0000
  14.500   1.2363   0.07671   0.07087  -0.0488   0.3978   1.0000
  14.750   1.2532   0.07725   0.07144  -0.0486   0.3852   1.0000
  15.000   1.2759   0.07712   0.07129  -0.0485   0.3711   1.0000
  15.250   1.3043   0.07624   0.07030  -0.0486   0.3514   1.0000
  15.500   1.3159   0.07728   0.07125  -0.0481   0.3312   1.0000
  15.750   1.3251   0.07857   0.07245  -0.0474   0.3109   1.0000
  16.000   1.3288   0.08045   0.07419  -0.0464   0.2883   1.0000
  16.250   1.3284   0.08285   0.07649  -0.0454   0.2657   1.0000
  16.500   1.3241   0.08573   0.07924  -0.0443   0.2433   1.0000
  16.750   1.3194   0.08873   0.08213  -0.0433   0.2217   1.0000
  17.000   1.3133   0.09193   0.08523  -0.0424   0.2016   1.0000
  17.250   1.3049   0.09546   0.08863  -0.0415   0.1788   1.0000
  17.500   1.2969   0.09902   0.09208  -0.0407   0.1584   1.0000
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