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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 50,000
Max Cl/Cd: 43.21 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe198-il-50000-n5.txt
Download as CSV file: xf-goe198-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 198 (L.F.G. 5294) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3068   0.11465   0.10811  -0.0220   1.0000   0.0762
  -7.500  -0.3163   0.11364   0.10719  -0.0198   1.0000   0.0774
  -7.250  -0.3246   0.11260   0.10623  -0.0183   1.0000   0.0787
  -7.000  -0.3314   0.11170   0.10541  -0.0182   1.0000   0.0800
  -6.750  -0.3364   0.11117   0.10494  -0.0197   1.0000   0.0809
  -6.250  -0.2928   0.10231   0.09605  -0.0284   0.9878   0.0833
  -6.000  -0.2699   0.09815   0.09185  -0.0318   0.9818   0.0855
  -5.750  -0.2450   0.09454   0.08821  -0.0369   0.9746   0.0882
  -5.500  -0.2169   0.09144   0.08502  -0.0441   0.9667   0.0917
  -5.250  -0.1724   0.08876   0.08218  -0.0581   0.9594   0.0946
  -5.000  -0.1641   0.08439   0.07788  -0.0552   0.9533   0.0968
  -4.750  -0.1397   0.08100   0.07446  -0.0582   0.9475   0.1011
  -4.500  -0.0918   0.07921   0.07242  -0.0710   0.9399   0.1081
  -4.250  -0.0661   0.07522   0.06842  -0.0745   0.9338   0.1098
  -4.000  -0.0417   0.07131   0.06452  -0.0760   0.9296   0.1132
  -3.750  -0.0170   0.06881   0.06196  -0.0789   0.9213   0.1185
  -3.500   0.0330   0.06592   0.05886  -0.0889   0.9159   0.1260
  -3.250   0.0554   0.06291   0.05586  -0.0898   0.9096   0.1314
  -3.000   0.0938   0.06043   0.05325  -0.0956   0.9026   0.1437
  -2.750   0.1365   0.05767   0.05036  -0.1015   0.8984   0.1595
  -2.500   0.1661   0.05579   0.04839  -0.1045   0.8896   0.1747
  -2.250   0.2028   0.05315   0.04571  -0.1083   0.8845   0.1926
  -1.250   0.3935   0.04363   0.03472  -0.1286   0.8580   0.0928
  -1.000   0.4353   0.04156   0.03247  -0.1320   0.8527   0.0903
  -0.750   0.4681   0.04010   0.03077  -0.1335   0.8433   0.0860
  -0.500   0.5149   0.03841   0.02856  -0.1366   0.8373   0.0808
  -0.250   0.5447   0.03725   0.02722  -0.1372   0.8264   0.0798
   0.000   0.5881   0.03561   0.02528  -0.1396   0.8201   0.0790
   0.500   0.6482   0.03379   0.02295  -0.1396   0.7954   0.0825
   0.750   0.6860   0.03244   0.02145  -0.1406   0.7867   0.0853
   1.000   0.7147   0.03165   0.02045  -0.1400   0.7740   0.0866
   1.250   0.7417   0.03107   0.01965  -0.1391   0.7616   0.0886
   1.500   0.7729   0.03035   0.01871  -0.1388   0.7524   0.0919
   1.750   0.8012   0.02974   0.01804  -0.1382   0.7420   0.0987
   2.000   0.8265   0.02941   0.01764  -0.1373   0.7299   0.1065
   2.250   0.8567   0.02876   0.01699  -0.1370   0.7203   0.1160
   2.500   0.8854   0.02829   0.01654  -0.1367   0.7093   0.1372
   2.750   0.9121   0.02791   0.01643  -0.1363   0.6966   0.1895
   3.000   0.9336   0.02641   0.01618  -0.1345   0.6850   1.0000
   3.250   0.9643   0.02625   0.01569  -0.1340   0.6747   1.0000
   3.500   0.9895   0.02641   0.01571  -0.1331   0.6610   1.0000
   3.750   1.0150   0.02657   0.01576  -0.1323   0.6471   1.0000
   4.000   1.0411   0.02670   0.01579  -0.1315   0.6333   1.0000
   4.250   1.0678   0.02683   0.01583  -0.1308   0.6196   1.0000
   4.500   1.0950   0.02695   0.01587  -0.1302   0.6060   1.0000
   4.750   1.1226   0.02709   0.01594  -0.1296   0.5923   1.0000
   5.000   1.1504   0.02725   0.01601  -0.1290   0.5785   1.0000
   5.250   1.1753   0.02762   0.01635  -0.1282   0.5634   1.0000
   5.500   1.1999   0.02800   0.01670  -0.1274   0.5473   1.0000
   5.750   1.2237   0.02840   0.01703  -0.1263   0.5302   1.0000
   6.000   1.2463   0.02884   0.01742  -0.1252   0.5126   1.0000
   6.250   1.2675   0.02937   0.01794  -0.1239   0.4954   1.0000
   6.500   1.2873   0.03000   0.01858  -0.1225   0.4792   1.0000
   6.750   1.3068   0.03071   0.01938  -0.1213   0.4651   1.0000
   7.000   1.3271   0.03144   0.02020  -0.1202   0.4531   1.0000
   7.250   1.3474   0.03209   0.02094  -0.1190   0.4410   1.0000
   7.500   1.3664   0.03271   0.02159  -0.1176   0.4281   1.0000
   7.750   1.3829   0.03341   0.02237  -0.1159   0.4144   1.0000
   8.000   1.3977   0.03418   0.02324  -0.1140   0.4008   1.0000
   8.250   1.4133   0.03499   0.02417  -0.1122   0.3888   1.0000
   8.500   1.4299   0.03575   0.02500  -0.1106   0.3780   1.0000
   8.750   1.4468   0.03651   0.02584  -0.1090   0.3678   1.0000
   9.000   1.4599   0.03751   0.02700  -0.1071   0.3572   1.0000
   9.250   1.4731   0.03841   0.02801  -0.1051   0.3462   1.0000
   9.500   1.4845   0.03935   0.02905  -0.1028   0.3353   1.0000
   9.750   1.4901   0.04062   0.03049  -0.1000   0.3235   1.0000
  10.000   1.4936   0.04197   0.03195  -0.0972   0.3098   1.0000
  10.250   1.4957   0.04349   0.03357  -0.0944   0.2958   1.0000
  10.500   1.4975   0.04516   0.03537  -0.0918   0.2823   1.0000
  10.750   1.4965   0.04715   0.03761  -0.0894   0.2679   1.0000
  11.000   1.4934   0.04945   0.04012  -0.0871   0.2518   1.0000
  11.250   1.4886   0.05213   0.04304  -0.0852   0.2333   1.0000
  11.500   1.4831   0.05503   0.04610  -0.0835   0.2124   1.0000
  11.750   1.4763   0.05813   0.04919  -0.0818   0.1918   1.0000
  12.000   1.4681   0.06159   0.05260  -0.0805   0.1736   1.0000
  12.250   1.4589   0.06538   0.05632  -0.0794   0.1595   1.0000
  12.500   1.4496   0.06937   0.06024  -0.0785   0.1488   1.0000
  12.750   1.4417   0.07339   0.06432  -0.0779   0.1396   1.0000
  13.000   1.4344   0.07742   0.06836  -0.0774   0.1325   1.0000
  13.250   1.4285   0.08144   0.07249  -0.0771   0.1258   1.0000
  13.500   1.4226   0.08543   0.07646  -0.0770   0.1205   1.0000
  13.750   1.4186   0.08942   0.08062  -0.0770   0.1145   1.0000
  14.000   1.4130   0.09352   0.08471  -0.0773   0.1091   1.0000
  14.250   1.4072   0.09797   0.08930  -0.0779   0.1031   1.0000
  14.500   1.4003   0.10248   0.09382  -0.0788   0.0972   1.0000
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