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GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 366 AIRFOIL (goe366-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.5 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe366-il-1000000.txt
Download as CSV file: xf-goe366-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 366 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0649   0.09541   0.09318  -0.0931   0.8444   0.0166
 -10.500   0.0722   0.09281   0.09056  -0.0936   0.8351   0.0167
 -10.250  -0.0114   0.10235   0.10014  -0.0892   0.8699   0.0166
 -10.000  -0.0024   0.09988   0.09760  -0.0897   0.8606   0.0167
  -9.750   0.0069   0.09743   0.09514  -0.0906   0.8507   0.0167
  -9.500   0.0159   0.09506   0.09272  -0.0916   0.8408   0.0168
  -9.250   0.0250   0.09270   0.09032  -0.0926   0.8294   0.0170
  -9.000   0.0342   0.09034   0.08791  -0.0937   0.8176   0.0171
  -8.750   0.0433   0.08798   0.08551  -0.0948   0.8061   0.0174
  -8.500   0.0525   0.08558   0.08305  -0.0961   0.7946   0.0176
  -8.250   0.0618   0.08312   0.08055  -0.0975   0.7845   0.0179
  -8.000   0.0710   0.08066   0.07803  -0.0989   0.7753   0.0183
  -7.750   0.0807   0.07806   0.07542  -0.1006   0.7679   0.0187
  -7.500   0.0900   0.07532   0.07264  -0.1032   0.7606   0.0190
  -7.250   0.0979   0.07266   0.06996  -0.1061   0.7545   0.0191
  -7.000   0.1117   0.06955   0.06683  -0.1113   0.7486   0.0191
  -6.750   0.1291   0.06615   0.06338  -0.1171   0.7430   0.0192
  -6.500   0.1492   0.06256   0.05975  -0.1229   0.7384   0.0192
  -6.000   0.1852   0.05599   0.05311  -0.1294   0.7289   0.0193
  -5.750   0.2020   0.05373   0.05080  -0.1306   0.7240   0.0194
  -5.500   0.2218   0.05136   0.04843  -0.1326   0.7201   0.0195
  -5.250   0.2433   0.04897   0.04601  -0.1351   0.7154   0.0196
  -5.000   0.2661   0.04660   0.04357  -0.1378   0.7106   0.0199
  -4.750   0.2903   0.04419   0.04108  -0.1405   0.7058   0.0201
  -4.500   0.3162   0.04168   0.03852  -0.1432   0.7017   0.0205
  -4.250   0.3429   0.03916   0.03593  -0.1458   0.6966   0.0211
  -4.000   0.3764   0.03613   0.03272  -0.1491   0.6914   0.0220
  -3.750   0.4083   0.03321   0.02961  -0.1513   0.6867   0.0221
  -3.500   0.4376   0.03060   0.02685  -0.1527   0.6816   0.0221
  -3.250   0.4622   0.02785   0.02396  -0.1537   0.6756   0.0222
  -3.000   0.4855   0.02628   0.02231  -0.1542   0.6692   0.0224
  -2.750   0.5108   0.02491   0.02088  -0.1548   0.6616   0.0225
  -2.500   0.5359   0.02367   0.01952  -0.1551   0.6533   0.0228
  -2.250   0.5627   0.02235   0.01811  -0.1555   0.6438   0.0231
  -2.000   0.5893   0.02106   0.01667  -0.1556   0.6322   0.0237
  -1.750   0.6215   0.01936   0.01448  -0.1548   0.6175   0.0253
  -1.500   0.6457   0.01756   0.01249  -0.1548   0.5966   0.0256
  -1.250   0.6689   0.01683   0.01160  -0.1544   0.5718   0.0258
  -1.000   0.6929   0.01627   0.01087  -0.1540   0.5513   0.0260
  -0.750   0.7177   0.01573   0.01017  -0.1536   0.5349   0.0264
  -0.250   0.7714   0.01511   0.00903  -0.1524   0.5103   0.0288
   0.000   0.7969   0.01389   0.00767  -0.1522   0.5005   0.0292
   0.250   0.8230   0.01335   0.00709  -0.1521   0.4917   0.0297
   0.500   0.8488   0.01302   0.00668  -0.1518   0.4837   0.0303
   0.750   0.8763   0.01318   0.00663  -0.1514   0.4765   0.0327
   1.000   0.9018   0.01233   0.00573  -0.1512   0.4689   0.0338
   1.250   0.9285   0.01207   0.00546  -0.1511   0.4624   0.0353
   1.500   0.9547   0.01184   0.00513  -0.1508   0.4554   0.0386
   1.750   0.9804   0.01185   0.00508  -0.1504   0.4488   0.0416
   2.000   1.0070   0.01152   0.00477  -0.1503   0.4433   0.0456
   2.250   1.0325   0.01142   0.00465  -0.1500   0.4371   0.0517
   3.000   1.1111   0.01106   0.00410  -0.1487   0.4201   0.0332
   3.250   1.1363   0.01111   0.00412  -0.1482   0.4145   0.0328
   3.500   1.1627   0.01103   0.00406  -0.1481   0.4098   0.0330
   3.750   1.1881   0.01103   0.00404  -0.1477   0.4046   0.0336
   4.000   1.2121   0.01114   0.00413  -0.1471   0.3989   0.0342
   4.250   1.2382   0.01118   0.00419  -0.1469   0.3946   0.0357
   4.500   1.2628   0.01128   0.00429  -0.1464   0.3889   0.0368
   4.750   1.2856   0.01147   0.00442  -0.1456   0.3827   0.0377
   5.000   1.3108   0.01155   0.00452  -0.1453   0.3787   0.0404
   5.250   1.3347   0.01167   0.00465  -0.1447   0.3743   0.0466
   5.500   1.3557   0.01055   0.00517  -0.1440   0.3699   1.0000
   5.750   1.3769   0.01079   0.00537  -0.1428   0.3649   1.0000
   6.000   1.4005   0.01096   0.00552  -0.1422   0.3605   1.0000
   6.250   1.4224   0.01118   0.00572  -0.1413   0.3557   1.0000
   6.500   1.4429   0.01147   0.00597  -0.1401   0.3508   1.0000
   6.750   1.4654   0.01169   0.00620  -0.1394   0.3473   1.0000
   7.000   1.4881   0.01190   0.00641  -0.1387   0.3437   1.0000
   7.250   1.5096   0.01216   0.00667  -0.1378   0.3398   1.0000
   7.500   1.5295   0.01248   0.00697  -0.1366   0.3358   1.0000
   7.750   1.5502   0.01278   0.00728  -0.1356   0.3321   1.0000
   8.000   1.5726   0.01301   0.00753  -0.1350   0.3285   1.0000
   8.250   1.5930   0.01333   0.00784  -0.1340   0.3239   1.0000
   8.500   1.6109   0.01376   0.00825  -0.1326   0.3184   1.0000
   8.750   1.6323   0.01404   0.00855  -0.1319   0.3140   1.0000
   9.000   1.6523   0.01439   0.00890  -0.1309   0.3092   1.0000
   9.250   1.6704   0.01484   0.00934  -0.1297   0.3044   1.0000
   9.500   1.6890   0.01526   0.00978  -0.1286   0.3002   1.0000
   9.750   1.7093   0.01562   0.01017  -0.1278   0.2959   1.0000
  10.000   1.7266   0.01612   0.01066  -0.1265   0.2902   1.0000
  10.250   1.7434   0.01667   0.01120  -0.1253   0.2844   1.0000
  10.500   1.7617   0.01714   0.01170  -0.1243   0.2782   1.0000
  11.000   1.7938   0.01837   0.01292  -0.1217   0.2650   1.0000
  11.250   1.8074   0.01913   0.01367  -0.1202   0.2578   1.0000
  11.500   1.8228   0.01981   0.01436  -0.1189   0.2504   1.0000
  11.750   1.8335   0.02079   0.01530  -0.1171   0.2406   1.0000
  12.000   1.8458   0.02169   0.01618  -0.1156   0.2303   1.0000
  12.250   1.8551   0.02279   0.01726  -0.1138   0.2190   1.0000
  12.500   1.8598   0.02423   0.01863  -0.1115   0.2034   1.0000
  12.750   1.8585   0.02614   0.02043  -0.1087   0.1839   1.0000
  13.000   1.8529   0.02843   0.02261  -0.1057   0.1615   1.0000
  13.250   1.8456   0.03100   0.02507  -0.1028   0.1422   1.0000
  13.500   1.8421   0.03339   0.02741  -0.1004   0.1293   1.0000
  13.750   1.8401   0.03574   0.02974  -0.0984   0.1200   1.0000
  14.000   1.8423   0.03782   0.03184  -0.0969   0.1138   1.0000
  14.250   1.8416   0.04022   0.03425  -0.0953   0.1075   1.0000
  14.500   1.8443   0.04234   0.03641  -0.0940   0.1025   1.0000
  14.750   1.8414   0.04505   0.03912  -0.0925   0.0965   1.0000
  15.000   1.8431   0.04738   0.04150  -0.0914   0.0911   1.0000
  15.250   1.8368   0.05058   0.04469  -0.0901   0.0836   1.0000
  15.500   1.8270   0.05422   0.04832  -0.0887   0.0740   1.0000
  15.750   1.8132   0.05844   0.05252  -0.0875   0.0639   1.0000
  16.000   1.7951   0.06335   0.05743  -0.0864   0.0543   1.0000
  16.250   1.7756   0.06858   0.06268  -0.0856   0.0455   1.0000
  16.500   1.7509   0.07466   0.06878  -0.0851   0.0361   1.0000
  16.750   1.7222   0.08148   0.07562  -0.0849   0.0254   1.0000
  17.000   1.7014   0.08737   0.08157  -0.0850   0.0209   1.0000
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