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UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.27 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua79sf18-il-1000000.txt
Download as CSV file: xf-ua79sf18-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.0994   0.15332   0.15024  -0.1209   0.7833   0.0052
 -16.500  -0.0933   0.14978   0.14670  -0.1226   0.7829   0.0052
  -6.750  -0.1194   0.01853   0.01297  -0.1293   0.7636   0.0085
  -6.500  -0.0943   0.01590   0.01016  -0.1284   0.7632   0.0054
  -6.250  -0.0785   0.01517   0.00936  -0.1266   0.7626   0.0054
  -6.000  -0.0605   0.01472   0.00887  -0.1252   0.7620   0.0053
  -5.750  -0.0447   0.01416   0.00825  -0.1235   0.7614   0.0054
  -5.500  -0.0263   0.01373   0.00777  -0.1223   0.7608   0.0055
  -5.250  -0.0067   0.01334   0.00735  -0.1212   0.7602   0.0060
  -5.000   0.0150   0.01304   0.00702  -0.1205   0.7597   0.0066
  -4.750   0.0380   0.01280   0.00674  -0.1200   0.7592   0.0072
  -4.500   0.0620   0.01260   0.00649  -0.1197   0.7587   0.0077
  -4.250   0.0861   0.01239   0.00623  -0.1194   0.7582   0.0083
  -4.000   0.1108   0.01220   0.00602  -0.1192   0.7577   0.0106
  -3.750   0.1337   0.01188   0.00581  -0.1188   0.7572   0.0405
  -3.500   0.1475   0.01086   0.00545  -0.1173   0.7566   0.2219
  -3.250   0.1622   0.00977   0.00511  -0.1161   0.7559   0.4329
  -3.000   0.1822   0.00943   0.00532  -0.1153   0.7550   0.6179
  -2.750   0.2098   0.00977   0.00565  -0.1154   0.7544   0.6393
  -2.500   0.2372   0.00998   0.00585  -0.1156   0.7537   0.6511
  -2.250   0.2640   0.01023   0.00615  -0.1154   0.7527   0.6656
  -2.000   0.2916   0.01034   0.00625  -0.1157   0.7515   0.6711
  -1.750   0.3196   0.01043   0.00630  -0.1160   0.7504   0.6751
  -1.500   0.3476   0.01040   0.00628  -0.1164   0.7494   0.6787
  -1.250   0.3762   0.01044   0.00632  -0.1169   0.7485   0.6816
  -1.000   0.4048   0.01047   0.00632  -0.1174   0.7476   0.6838
  -0.750   0.4339   0.01048   0.00630  -0.1181   0.7468   0.6856
  -0.500   0.4631   0.01050   0.00630  -0.1187   0.7461   0.6872
  -0.250   0.4927   0.01053   0.00629  -0.1195   0.7454   0.6885
   0.000   0.5226   0.01039   0.00614  -0.1203   0.7446   0.6901
   0.250   0.5533   0.01028   0.00601  -0.1212   0.7438   0.6908
   0.500   0.5844   0.01019   0.00590  -0.1223   0.7431   0.6911
   0.750   0.6152   0.01017   0.00585  -0.1233   0.7422   0.6914
   1.000   0.6430   0.01020   0.00588  -0.1238   0.7410   0.6916
   1.250   0.6686   0.01015   0.00586  -0.1238   0.7392   0.6920
   1.500   0.6960   0.01008   0.00581  -0.1241   0.7372   0.6925
   1.750   0.7252   0.00995   0.00569  -0.1247   0.7355   0.6930
   2.000   0.7562   0.00975   0.00549  -0.1257   0.7338   0.6932
   2.250   0.7880   0.00951   0.00524  -0.1268   0.7323   0.6936
   2.500   0.8213   0.00926   0.00498  -0.1283   0.7308   0.6942
   2.750   0.8545   0.00908   0.00478  -0.1297   0.7293   0.6949
   3.000   0.8808   0.00907   0.00480  -0.1298   0.7275   0.6954
   3.250   0.9057   0.00906   0.00486  -0.1297   0.7254   0.6956
   3.500   0.9325   0.00901   0.00484  -0.1299   0.7234   0.6957
   3.750   0.9621   0.00882   0.00467  -0.1306   0.7209   0.6958
   4.000   0.9906   0.00813   0.00395  -0.1307   0.7101   0.6959
   4.250   1.0185   0.00787   0.00366  -0.1309   0.7025   0.6960
   4.500   1.0328   0.00775   0.00357  -0.1284   0.6788   0.6962
   4.750   1.0173   0.00801   0.00353  -0.1194   0.6275   0.6964
   5.000   0.9912   0.00881   0.00415  -0.1090   0.5837   0.6966
   5.250   0.9464   0.01067   0.00579  -0.0964   0.5444   0.6968
   5.500   0.9479   0.01159   0.00668  -0.0926   0.5296   0.6970
   5.750   0.9049   0.01414   0.00892  -0.0818   0.4711   0.6972
   6.000   0.8892   0.01577   0.01034  -0.0755   0.4315   0.6974
   6.250   0.8596   0.01800   0.01216  -0.0674   0.3577   0.6976
   6.750   0.8305   0.02169   0.01498  -0.0563   0.2045   0.6983
   7.000   0.7987   0.02465   0.01712  -0.0489   0.0524   0.6984
   7.250   0.8069   0.02572   0.01804  -0.0469   0.0081   0.6985
   7.500   0.8249   0.02629   0.01863  -0.0462   0.0062   0.6986
   7.750   0.8433   0.02684   0.01922  -0.0455   0.0054   0.6987
   8.000   0.8607   0.02746   0.01988  -0.0447   0.0050   0.6988
   8.250   0.8771   0.02815   0.02062  -0.0438   0.0045   0.6990
   8.500   0.8938   0.02883   0.02134  -0.0430   0.0045   0.6992
   8.750   0.9089   0.02961   0.02218  -0.0420   0.0042   0.6993
   9.000   0.9235   0.03045   0.02307  -0.0409   0.0042   0.6995
   9.250   0.9366   0.03141   0.02411  -0.0397   0.0042   0.6997
   9.500   0.9499   0.03238   0.02513  -0.0385   0.0044   0.6999
   9.750   0.9619   0.03345   0.02626  -0.0373   0.0046   0.7000
  10.000   0.9684   0.03494   0.02784  -0.0354   0.0049   0.7002
  10.250   0.9830   0.03588   0.02880  -0.0346   0.0055   0.7005
  10.500   1.0065   0.03622   0.02923  -0.0344   0.0075   0.7007
  13.500   1.1762   0.05206   0.04561  -0.0243   0.0051   0.7047
  13.750   1.1792   0.05398   0.04766  -0.0230   0.0050   0.7052
  14.000   1.1735   0.05625   0.05008  -0.0212   0.0050   0.7059
  14.250   1.1733   0.05844   0.05241  -0.0200   0.0049   0.7065
  14.500   1.1716   0.06078   0.05489  -0.0189   0.0047   0.7072
  14.750   1.1707   0.06318   0.05740  -0.0181   0.0043   0.7080
  15.000   1.1821   0.06506   0.05939  -0.0177   0.0043   0.7087
  15.250   1.1872   0.06733   0.06177  -0.0172   0.0040   0.7095
  15.500   1.1920   0.06970   0.06422  -0.0169   0.0036   0.7103
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