Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.26 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gu255118-il-1000000.txt
Download as CSV file: xf-gu255118-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.1895   0.07921   0.07549  -0.1569   0.6181   0.0223
 -12.000   0.1937   0.07645   0.07274  -0.1576   0.6177   0.0224
 -11.750   0.2032   0.07482   0.07112  -0.1580   0.6170   0.0227
 -11.500   0.2065   0.07193   0.06824  -0.1588   0.6164   0.0228
 -11.250  -0.1886   0.03133   0.02676  -0.1808   0.6193   0.0187
 -11.000  -0.1895   0.03054   0.02594  -0.1777   0.6185   0.0189
 -10.750  -0.1885   0.02993   0.02532  -0.1744   0.6178   0.0190
 -10.500  -0.2037   0.02857   0.02382  -0.1687   0.6172   0.0191
 -10.250  -0.1938   0.02809   0.02332  -0.1665   0.6164   0.0192
 -10.000  -0.1804   0.02775   0.02296  -0.1649   0.6156   0.0194
  -9.750  -0.1661   0.02744   0.02264  -0.1633   0.6148   0.0197
  -9.500  -0.1566   0.02668   0.02179  -0.1610   0.6140   0.0200
  -9.250  -0.1532   0.02518   0.02010  -0.1579   0.6132   0.0202
  -9.000  -0.1485   0.02356   0.01826  -0.1549   0.6124   0.0204
  -8.750  -0.1405   0.02207   0.01655  -0.1521   0.6116   0.0206
  -8.500  -0.1274   0.02095   0.01525  -0.1501   0.6108   0.0209
  -8.250  -0.1123   0.01989   0.01401  -0.1483   0.6101   0.0212
  -8.000  -0.0949   0.01905   0.01301  -0.1468   0.6093   0.0215
  -7.750  -0.0751   0.01857   0.01240  -0.1456   0.6086   0.0218
  -7.500  -0.0546   0.01812   0.01182  -0.1445   0.6077   0.0220
  -7.250  -0.0366   0.01670   0.01024  -0.1433   0.6070   0.0225
  -7.000  -0.0147   0.01606   0.00957  -0.1426   0.6061   0.0229
  -6.750   0.0085   0.01575   0.00922  -0.1421   0.6052   0.0233
  -6.500   0.0322   0.01548   0.00891  -0.1417   0.6042   0.0238
  -6.250   0.0561   0.01515   0.00854  -0.1412   0.6035   0.0242
  -6.000   0.0795   0.01475   0.00810  -0.1406   0.6032   0.0246
  -5.750   0.1031   0.01437   0.00768  -0.1401   0.6029   0.0250
  -5.500   0.1269   0.01404   0.00731  -0.1395   0.6025   0.0255
  -5.250   0.1509   0.01375   0.00699  -0.1390   0.6021   0.0259
  -5.000   0.1752   0.01354   0.00674  -0.1386   0.6017   0.0262
  -4.750   0.1966   0.01301   0.00619  -0.1376   0.6012   0.0268
  -4.500   0.2180   0.01260   0.00578  -0.1366   0.6007   0.0274
  -4.250   0.2414   0.01238   0.00557  -0.1360   0.6002   0.0282
  -4.000   0.2654   0.01221   0.00539  -0.1355   0.5996   0.0290
  -3.750   0.2891   0.01202   0.00518  -0.1349   0.5990   0.0296
  -3.500   0.3131   0.01185   0.00500  -0.1344   0.5985   0.0303
  -3.250   0.3375   0.01171   0.00484  -0.1339   0.5980   0.0309
  -3.000   0.3624   0.01160   0.00472  -0.1336   0.5975   0.0314
  -2.750   0.3845   0.01133   0.00442  -0.1327   0.5970   0.0326
  -2.500   0.4090   0.01120   0.00429  -0.1323   0.5966   0.0341
  -2.250   0.4341   0.01112   0.00420  -0.1320   0.5961   0.0354
  -2.000   0.4595   0.01105   0.00413  -0.1318   0.5957   0.0367
  -1.750   0.4843   0.01094   0.00401  -0.1314   0.5952   0.0390
  -1.500   0.5095   0.01087   0.00395  -0.1312   0.5948   0.0419
  -1.250   0.5347   0.01080   0.00390  -0.1309   0.5944   0.0496
  -1.000   0.5559   0.01050   0.00385  -0.1299   0.5940   0.1244
  -0.750   0.5739   0.01003   0.00383  -0.1284   0.5936   0.2700
  -0.500   0.5905   0.00956   0.00384  -0.1267   0.5931   0.4342
   0.000   0.6318   0.00920   0.00396  -0.1244   0.5923   0.6062
   0.250   0.6529   0.00910   0.00404  -0.1233   0.5919   0.6669
   0.500   0.6726   0.00901   0.00412  -0.1218   0.5915   0.7313
   0.750   0.6919   0.00891   0.00422  -0.1202   0.5911   0.7957
   1.000   0.7975   0.00892   0.00458  -0.1378   0.5908   0.9321
   1.250   0.8443   0.00919   0.00484  -0.1421   0.5904   0.9559
   1.500   0.8836   0.00945   0.00507  -0.1449   0.5899   0.9638
   1.750   0.9167   0.00971   0.00531  -0.1465   0.5892   0.9700
   2.000   0.9559   0.00998   0.00557  -0.1495   0.5885   0.9724
   2.250   0.9930   0.01011   0.00569  -0.1520   0.5883   0.9757
   2.500   1.0240   0.01027   0.00585  -0.1531   0.5881   0.9809
   2.750   1.0615   0.01040   0.00597  -0.1557   0.5879   0.9830
   3.000   1.1001   0.01052   0.00609  -0.1586   0.5877   0.9848
   3.250   1.1373   0.01064   0.00623  -0.1612   0.5874   0.9869
   3.500   1.1734   0.01078   0.00637  -0.1636   0.5872   0.9894
   3.750   1.2080   0.01092   0.00653  -0.1657   0.5869   0.9922
   4.000   1.2432   0.01105   0.00667  -0.1679   0.5866   0.9941
   4.250   1.2806   0.01116   0.00679  -0.1706   0.5863   0.9959
   4.500   1.3169   0.01126   0.00692  -0.1731   0.5858   0.9979
   4.750   1.3530   0.01137   0.00705  -0.1756   0.5854   0.9996
   5.000   1.3769   0.01147   0.00718  -0.1754   0.5847   1.0000
   5.250   1.3959   0.01157   0.00731  -0.1742   0.5839   1.0000
   5.500   1.4150   0.01168   0.00744  -0.1729   0.5832   1.0000
   5.750   1.4345   0.01180   0.00759  -0.1718   0.5824   1.0000
   6.000   1.4541   0.01193   0.00775  -0.1707   0.5818   1.0000
   6.250   1.4739   0.01205   0.00790  -0.1696   0.5811   1.0000
   6.500   1.4939   0.01218   0.00805  -0.1686   0.5805   1.0000
   6.750   1.5145   0.01228   0.00818  -0.1676   0.5797   1.0000
   7.000   1.5358   0.01237   0.00829  -0.1669   0.5789   1.0000
   7.250   1.5586   0.01241   0.00835  -0.1664   0.5779   1.0000
   7.500   1.5840   0.01242   0.00835  -0.1664   0.5767   1.0000
   7.750   1.6107   0.01252   0.00846  -0.1668   0.5752   1.0000
   8.000   1.6215   0.01264   0.00862  -0.1638   0.5725   1.0000
   8.250   1.6254   0.01266   0.00870  -0.1594   0.5708   1.0000
   8.500   1.6234   0.01257   0.00866  -0.1536   0.5682   1.0000
   8.750   1.6289   0.01251   0.00861  -0.1494   0.5661   1.0000
   9.000   1.6426   0.01234   0.00845  -0.1469   0.5635   1.0000
   9.250   1.6664   0.01223   0.00829  -0.1466   0.5594   1.0000
   9.500   1.6587   0.01240   0.00854  -0.1401   0.5571   1.0000
   9.750   1.6598   0.01264   0.00885  -0.1357   0.5546   1.0000
  10.000   1.6621   0.01282   0.00908  -0.1315   0.5503   1.0000
  10.250   1.6728   0.01303   0.00929  -0.1291   0.5466   1.0000
  10.500   1.6722   0.01365   0.00997  -0.1250   0.5415   1.0000
  10.750   1.6719   0.01444   0.01083  -0.1213   0.5353   1.0000
  11.000   1.6759   0.01525   0.01166  -0.1185   0.5287   1.0000
  11.250   1.6783   0.01633   0.01282  -0.1157   0.5205   1.0000
  11.500   1.6766   0.01772   0.01424  -0.1126   0.5085   1.0000
  11.750   1.6564   0.02026   0.01674  -0.1073   0.4885   1.0000
  12.000   1.6223   0.02389   0.02031  -0.1009   0.4670   1.0000
  12.250   1.5887   0.02777   0.02412  -0.0948   0.4494   1.0000
  12.500   1.5563   0.03178   0.02808  -0.0893   0.4320   1.0000
  12.750   1.5253   0.03589   0.03213  -0.0842   0.4110   1.0000
  13.000   1.5009   0.03967   0.03585  -0.0800   0.3928   1.0000
  13.250   1.4720   0.04393   0.04002  -0.0756   0.3711   1.0000
  13.500   1.4551   0.04733   0.04333  -0.0724   0.3507   1.0000
  13.750   1.4358   0.05104   0.04693  -0.0692   0.3287   1.0000
  14.000   1.4244   0.05416   0.04998  -0.0668   0.3105   1.0000
  14.250   1.4125   0.05734   0.05303  -0.0644   0.2863   1.0000
  14.500   1.4016   0.06053   0.05611  -0.0622   0.2653   1.0000
  14.750   1.3916   0.06367   0.05911  -0.0601   0.2393   1.0000
  15.000   1.3826   0.06678   0.06208  -0.0582   0.2143   1.0000
  15.250   1.3720   0.07006   0.06519  -0.0563   0.1861   1.0000
  15.500   1.3686   0.07272   0.06772  -0.0549   0.1655   1.0000
  15.750   1.3620   0.07578   0.07065  -0.0535   0.1420   1.0000
  16.000   1.3518   0.07917   0.07383  -0.0519   0.1130   1.0000
  16.250   1.3490   0.08189   0.07644  -0.0508   0.0931   1.0000
  16.500   1.3391   0.08544   0.07982  -0.0495   0.0691   1.0000
  16.750   1.3301   0.08892   0.08313  -0.0482   0.0452   1.0000
<< Back to UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)

Polar data table (+)

Polar graphs


<< Back to UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)