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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 500,000
Max Cl/Cd: 105.76 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe342-il-500000-n5.txt
Download as CSV file: xf-goe342-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 342 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2117   0.09055   0.08824  -0.0492   0.9546   0.0096
  -7.750  -0.2018   0.08713   0.08479  -0.0516   0.9402   0.0097
  -7.500  -0.1929   0.08376   0.08140  -0.0540   0.9252   0.0099
  -7.250  -0.1793   0.08150   0.07911  -0.0558   0.9128   0.0101
  -7.000  -0.1647   0.07891   0.07648  -0.0584   0.9004   0.0103
  -6.750  -0.1485   0.07631   0.07383  -0.0612   0.8883   0.0109
  -6.500  -0.1305   0.07320   0.07067  -0.0649   0.8762   0.0118
  -6.250  -0.1102   0.06951   0.06692  -0.0698   0.8648   0.0121
  -6.000  -0.0843   0.06458   0.06191  -0.0772   0.8543   0.0125
  -5.500  -0.0378   0.05949   0.05669  -0.0844   0.8342   0.0133
  -5.250  -0.0109   0.05673   0.05386  -0.0888   0.8246   0.0145
  -5.000   0.0236   0.05244   0.04945  -0.0961   0.8159   0.0155
  -4.750   0.0576   0.04872   0.04564  -0.1024   0.8086   0.0163
  -4.500   0.0862   0.04646   0.04330  -0.1059   0.8012   0.0169
  -4.250   0.1193   0.04375   0.04049  -0.1105   0.7944   0.0182
  -4.000   0.1739   0.03817   0.03467  -0.1210   0.7880   0.0201
  -3.750   0.1940   0.03730   0.03377  -0.1211   0.7823   0.0209
  -3.500   0.2359   0.03538   0.03170  -0.1256   0.7770   0.0246
  -3.250   0.2755   0.03240   0.02853  -0.1297   0.7719   0.0248
  -3.000   0.3105   0.02957   0.02550  -0.1328   0.7673   0.0248
  -2.750   0.3452   0.02697   0.02272  -0.1354   0.7618   0.0249
  -2.500   0.3817   0.02320   0.01869  -0.1390   0.7566   0.0256
  -2.250   0.4085   0.02224   0.01767  -0.1400   0.7520   0.0263
  -2.000   0.4396   0.02080   0.01610  -0.1413   0.7472   0.0270
  -1.750   0.4715   0.01926   0.01439  -0.1426   0.7422   0.0276
  -1.500   0.5038   0.01771   0.01262  -0.1437   0.7364   0.0280
  -1.250   0.5363   0.01608   0.01072  -0.1447   0.7277   0.0276
  -1.000   0.5665   0.01510   0.00953  -0.1452   0.7186   0.0284
  -0.750   0.5974   0.01399   0.00820  -0.1458   0.7110   0.0283
  -0.500   0.6289   0.01266   0.00654  -0.1463   0.7053   0.0269
  -0.250   0.6588   0.01189   0.00560  -0.1466   0.6994   0.0268
   0.000   0.6877   0.01138   0.00496  -0.1468   0.6931   0.0271
   0.250   0.7164   0.01096   0.00446  -0.1470   0.6861   0.0275
   0.500   0.7447   0.01063   0.00404  -0.1470   0.6767   0.0280
   0.750   0.7728   0.01034   0.00368  -0.1470   0.6630   0.0284
   1.000   0.8003   0.01015   0.00339  -0.1469   0.6438   0.0291
   1.250   0.8273   0.01006   0.00320  -0.1466   0.6137   0.0301
   1.500   0.8522   0.01017   0.00301  -0.1460   0.5543   0.0303
   1.750   0.8763   0.01045   0.00298  -0.1454   0.4933   0.0303
   2.000   0.9012   0.01070   0.00300  -0.1450   0.4457   0.0304
   2.250   0.9266   0.01092   0.00305  -0.1446   0.4075   0.0306
   2.500   0.9524   0.01110   0.00310  -0.1444   0.3804   0.0310
   2.750   0.9787   0.01123   0.00316  -0.1442   0.3627   0.0316
   3.000   1.0050   0.01138   0.00327  -0.1439   0.3488   0.0323
   3.500   1.0581   0.01161   0.00343  -0.1436   0.3283   0.0348
   3.750   1.0842   0.01177   0.00357  -0.1433   0.3186   0.0377
   4.000   1.1105   0.01192   0.00372  -0.1431   0.3114   0.0392
   4.250   1.1366   0.01209   0.00388  -0.1428   0.3044   0.0407
   4.750   1.1851   0.01122   0.00448  -0.1419   0.2841   1.0000
   5.000   1.2106   0.01148   0.00469  -0.1415   0.2746   1.0000
   5.250   1.2363   0.01169   0.00489  -0.1412   0.2656   1.0000
   5.500   1.2617   0.01194   0.00513  -0.1408   0.2556   1.0000
   5.750   1.2866   0.01223   0.00539  -0.1403   0.2419   1.0000
   6.000   1.3103   0.01263   0.00568  -0.1397   0.2163   1.0000
   6.250   1.3270   0.01381   0.00638  -0.1381   0.1365   1.0000
   6.500   1.3477   0.01454   0.00696  -0.1371   0.1124   1.0000
   6.750   1.3698   0.01508   0.00746  -0.1362   0.0997   1.0000
   7.000   1.3927   0.01552   0.00788  -0.1355   0.0894   1.0000
   7.250   1.4150   0.01599   0.00833  -0.1347   0.0784   1.0000
   7.500   1.4367   0.01652   0.00881  -0.1338   0.0676   1.0000
   7.750   1.4578   0.01708   0.00933  -0.1328   0.0578   1.0000
   8.000   1.4789   0.01762   0.00986  -0.1318   0.0512   1.0000
   8.250   1.5000   0.01812   0.01039  -0.1308   0.0449   1.0000
   8.500   1.5192   0.01879   0.01101  -0.1295   0.0340   1.0000
   8.750   1.5347   0.01978   0.01186  -0.1278   0.0188   1.0000
   9.000   1.5520   0.02054   0.01266  -0.1262   0.0149   1.0000
   9.250   1.5683   0.02135   0.01352  -0.1244   0.0128   1.0000
   9.500   1.5844   0.02211   0.01436  -0.1226   0.0115   1.0000
   9.750   1.5997   0.02283   0.01517  -0.1207   0.0105   1.0000
  10.000   1.6119   0.02363   0.01605  -0.1183   0.0097   1.0000
  10.250   1.6224   0.02457   0.01708  -0.1157   0.0090   1.0000
  10.500   1.6301   0.02575   0.01836  -0.1128   0.0083   1.0000
  10.750   1.6409   0.02671   0.01942  -0.1105   0.0080   1.0000
  11.000   1.6504   0.02779   0.02061  -0.1081   0.0077   1.0000
  11.250   1.6589   0.02898   0.02191  -0.1058   0.0074   1.0000
  11.500   1.6665   0.03027   0.02330  -0.1035   0.0070   1.0000
  11.750   1.6735   0.03167   0.02480  -0.1012   0.0067   1.0000
  12.000   1.6797   0.03317   0.02640  -0.0991   0.0064   1.0000
  12.250   1.6837   0.03491   0.02825  -0.0969   0.0061   1.0000
  12.500   1.6835   0.03711   0.03056  -0.0946   0.0059   1.0000
  12.750   1.6849   0.03926   0.03283  -0.0926   0.0057   1.0000
  13.000   1.6877   0.04133   0.03504  -0.0909   0.0055   1.0000
  13.250   1.6884   0.04369   0.03753  -0.0893   0.0054   1.0000
  13.500   1.6878   0.04627   0.04025  -0.0878   0.0053   1.0000
  13.750   1.6861   0.04906   0.04318  -0.0865   0.0051   1.0000
  14.000   1.6829   0.05208   0.04634  -0.0854   0.0050   1.0000
  14.250   1.6788   0.05533   0.04974  -0.0844   0.0049   1.0000
  14.500   1.6734   0.05886   0.05342  -0.0837   0.0048   1.0000
  14.750   1.6670   0.06264   0.05734  -0.0833   0.0047   1.0000
  15.000   1.6599   0.06671   0.06155  -0.0831   0.0046   1.0000
  15.250   1.6515   0.07117   0.06616  -0.0834   0.0046   1.0000
  15.500   1.6425   0.07596   0.07110  -0.0840   0.0045   1.0000
  15.750   1.6326   0.08109   0.07637  -0.0850   0.0044   1.0000
  16.000   1.6218   0.08660   0.08203  -0.0865   0.0044   1.0000
  16.250   1.6101   0.09248   0.08806  -0.0883   0.0043   1.0000
  16.500   1.5977   0.09865   0.09438  -0.0904   0.0043   1.0000
  16.750   1.5848   0.10501   0.10088  -0.0927   0.0043   1.0000
  17.000   1.5717   0.11152   0.10753  -0.0953   0.0042   1.0000
  17.250   1.5585   0.11815   0.11430  -0.0981   0.0042   1.0000
  17.500   1.5455   0.12481   0.12109  -0.1010   0.0042   1.0000
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