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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.24 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe711-il-1000000.txt
Download as CSV file: xf-goe711-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0705   0.09027   0.08852  -0.0987   0.9588   0.0185
  -9.250  -0.0689   0.08656   0.08481  -0.1001   0.9538   0.0186
  -9.000  -0.0722   0.08206   0.08032  -0.1013   0.9479   0.0187
  -8.750  -0.0669   0.07984   0.07808  -0.1009   0.9426   0.0189
  -8.500  -0.0597   0.07763   0.07587  -0.1012   0.9364   0.0190
  -8.250  -0.0543   0.07517   0.07341  -0.1019   0.9299   0.0192
  -8.000  -0.0499   0.07250   0.07073  -0.1031   0.9233   0.0194
  -7.750  -0.0487   0.06963   0.06785  -0.1050   0.9154   0.0197
  -7.500  -0.0406   0.06605   0.06424  -0.1091   0.9085   0.0202
  -7.250  -0.0327   0.05581   0.05383  -0.1224   0.8989   0.0222
  -7.000  -0.0045   0.03527   0.03323  -0.1219   0.8689   0.0226
  -6.750  -0.0157   0.04523   0.04297  -0.1278   0.8826   0.0227
  -6.500   0.0026   0.04349   0.04117  -0.1284   0.8734   0.0229
  -6.250   0.0219   0.04169   0.03928  -0.1291   0.8640   0.0233
  -6.000   0.0420   0.03960   0.03706  -0.1299   0.8529   0.0238
  -5.750   0.0665   0.03338   0.03032  -0.1311   0.8416   0.0266
  -5.500   0.0804   0.02831   0.02496  -0.1316   0.8296   0.0271
  -5.250   0.1040   0.02729   0.02383  -0.1319   0.8164   0.0274
  -5.000   0.1283   0.02627   0.02269  -0.1321   0.8022   0.0279
  -4.750   0.1530   0.02515   0.02141  -0.1322   0.7869   0.0286
  -4.500   0.1823   0.02412   0.01990  -0.1315   0.7713   0.0316
  -4.250   0.2035   0.01982   0.01519  -0.1317   0.7570   0.0323
  -4.000   0.2297   0.01899   0.01426  -0.1319   0.7415   0.0328
  -3.750   0.2563   0.01831   0.01345  -0.1321   0.7255   0.0333
  -3.500   0.2832   0.01763   0.01262  -0.1322   0.7090   0.0342
  -3.250   0.3115   0.01493   0.00923  -0.1315   0.6942   0.0319
  -3.000   0.3387   0.01384   0.00802  -0.1315   0.6783   0.0310
  -2.750   0.3663   0.01312   0.00711  -0.1315   0.6628   0.0311
  -2.500   0.3940   0.01270   0.00653  -0.1315   0.6466   0.0314
  -2.250   0.4212   0.01196   0.00562  -0.1315   0.6297   0.0321
  -2.000   0.4482   0.01146   0.00503  -0.1315   0.6125   0.0326
  -1.750   0.4755   0.01120   0.00469  -0.1315   0.5956   0.0330
  -1.500   0.5028   0.01101   0.00442  -0.1315   0.5794   0.0334
  -1.250   0.5300   0.01087   0.00420  -0.1315   0.5629   0.0339
  -1.000   0.5572   0.01076   0.00400  -0.1315   0.5461   0.0344
  -0.750   0.5843   0.01067   0.00383  -0.1315   0.5297   0.0350
  -0.500   0.6115   0.01062   0.00370  -0.1316   0.5145   0.0358
  -0.250   0.6388   0.01062   0.00362  -0.1316   0.5001   0.0368
   0.000   0.6660   0.01064   0.00356  -0.1316   0.4860   0.0374
   0.250   0.6929   0.01056   0.00340  -0.1316   0.4718   0.0383
   0.750   0.7472   0.01057   0.00328  -0.1317   0.4449   0.0411
   1.000   0.7743   0.01062   0.00328  -0.1317   0.4335   0.0429
   1.250   0.8012   0.01071   0.00331  -0.1317   0.4225   0.0447
   1.500   0.8281   0.01076   0.00331  -0.1317   0.4119   0.0490
   1.750   0.8551   0.01083   0.00335  -0.1317   0.4024   0.0538
   2.000   0.8788   0.00935   0.00365  -0.1321   0.3931   0.7905
   2.250   0.9003   0.00905   0.00373  -0.1304   0.3849   1.0000
   2.500   0.9265   0.00924   0.00383  -0.1303   0.3765   1.0000
   2.750   0.9531   0.00940   0.00392  -0.1302   0.3693   1.0000
   3.000   0.9789   0.00960   0.00405  -0.1301   0.3619   1.0000
   3.250   1.0055   0.00975   0.00415  -0.1300   0.3552   1.0000
   3.500   1.0306   0.00998   0.00430  -0.1297   0.3472   1.0000
   3.750   1.0569   0.01013   0.00442  -0.1297   0.3411   1.0000
   4.000   1.0821   0.01034   0.00456  -0.1294   0.3347   1.0000
   4.250   1.1074   0.01053   0.00471  -0.1292   0.3285   1.0000
   4.500   1.1326   0.01071   0.00486  -0.1290   0.3225   1.0000
   4.750   1.1569   0.01094   0.00504  -0.1285   0.3171   1.0000
   5.000   1.1820   0.01111   0.00520  -0.1283   0.3134   1.0000
   5.250   1.2069   0.01128   0.00536  -0.1280   0.3094   1.0000
   5.500   1.2308   0.01150   0.00555  -0.1275   0.3052   1.0000
   5.750   1.2535   0.01176   0.00578  -0.1268   0.3005   1.0000
   6.000   1.2776   0.01192   0.00595  -0.1264   0.2974   1.0000
   6.250   1.2997   0.01212   0.00615  -0.1255   0.2934   1.0000
   6.500   1.3203   0.01240   0.00640  -0.1244   0.2886   1.0000
   6.750   1.3414   0.01267   0.00665  -0.1234   0.2837   1.0000
   7.000   1.3636   0.01290   0.00688  -0.1227   0.2785   1.0000
   7.250   1.3835   0.01324   0.00719  -0.1215   0.2716   1.0000
   7.500   1.4055   0.01350   0.00745  -0.1208   0.2668   1.0000
   7.750   1.4264   0.01381   0.00774  -0.1199   0.2607   1.0000
   8.000   1.4462   0.01418   0.00808  -0.1188   0.2546   1.0000
   8.250   1.4675   0.01448   0.00839  -0.1180   0.2488   1.0000
   8.500   1.4859   0.01493   0.00879  -0.1168   0.2410   1.0000
   8.750   1.5053   0.01534   0.00917  -0.1158   0.2318   1.0000
   9.000   1.5229   0.01585   0.00964  -0.1144   0.2211   1.0000
   9.250   1.5387   0.01645   0.01018  -0.1128   0.2088   1.0000
   9.500   1.5517   0.01722   0.01084  -0.1108   0.1918   1.0000
   9.750   1.5578   0.01840   0.01184  -0.1078   0.1647   1.0000
  10.000   1.5514   0.02033   0.01350  -0.1030   0.1250   1.0000
  10.250   1.5513   0.02197   0.01500  -0.0993   0.1013   1.0000
  10.500   1.5391   0.02445   0.01727  -0.0942   0.0549   1.0000
  10.750   1.5483   0.02562   0.01846  -0.0922   0.0484   1.0000
  11.000   1.5596   0.02667   0.01955  -0.0905   0.0429   1.0000
  11.250   1.5659   0.02811   0.02096  -0.0884   0.0298   1.0000
  11.500   1.5675   0.02992   0.02272  -0.0859   0.0174   1.0000
  11.750   1.5747   0.03140   0.02425  -0.0841   0.0156   1.0000
  12.000   1.5828   0.03286   0.02577  -0.0826   0.0146   1.0000
  12.250   1.5909   0.03437   0.02735  -0.0812   0.0140   1.0000
  12.500   1.5971   0.03610   0.02914  -0.0798   0.0134   1.0000
  12.750   1.6014   0.03806   0.03118  -0.0783   0.0128   1.0000
  13.000   1.6024   0.04043   0.03363  -0.0768   0.0122   1.0000
  13.250   1.6043   0.04280   0.03610  -0.0755   0.0119   1.0000
  13.500   1.6084   0.04504   0.03841  -0.0746   0.0116   1.0000
  13.750   1.6107   0.04753   0.04098  -0.0737   0.0113   1.0000
  14.000   1.6110   0.05028   0.04383  -0.0729   0.0111   1.0000
  14.250   1.6098   0.05331   0.04695  -0.0722   0.0108   1.0000
  14.500   1.6072   0.05660   0.05034  -0.0716   0.0105   1.0000
  14.750   1.6030   0.06018   0.05401  -0.0712   0.0103   1.0000
  15.000   1.5958   0.06421   0.05814  -0.0709   0.0101   1.0000
  15.250   1.5850   0.06879   0.06284  -0.0707   0.0099   1.0000
  15.500   1.5701   0.07408   0.06825  -0.0707   0.0097   1.0000
  15.750   1.5516   0.08001   0.07433  -0.0710   0.0096   1.0000
  16.000   1.5299   0.08650   0.08098  -0.0716   0.0094   1.0000
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