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GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 366 AIRFOIL (goe366-il)
Reynolds number: 500,000
Max Cl/Cd: 102.6 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe366-il-500000.txt
Download as CSV file: xf-goe366-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0234   0.09914   0.09648  -0.0941   0.9097   0.0214
  -9.500   0.0310   0.09663   0.09393  -0.0952   0.8991   0.0218
  -9.250   0.0380   0.09415   0.09142  -0.0968   0.8886   0.0220
  -9.000   0.1076   0.07833   0.07551  -0.1032   0.8426   0.0222
  -8.750   0.1205   0.07511   0.07229  -0.1024   0.8346   0.0223
  -8.500   0.1291   0.07236   0.06949  -0.1024   0.8277   0.0224
  -8.250   0.1371   0.06968   0.06681  -0.1028   0.8204   0.0225
  -8.000   0.1445   0.06707   0.06417  -0.1033   0.8135   0.0226
  -7.750   0.1517   0.06447   0.06154  -0.1041   0.8073   0.0228
  -7.500   0.1588   0.06186   0.05892  -0.1049   0.8004   0.0230
  -7.250   0.1658   0.05928   0.05629  -0.1058   0.7944   0.0233
  -7.000   0.1728   0.05667   0.05367  -0.1069   0.7884   0.0236
  -6.750   0.1795   0.05403   0.05103  -0.1081   0.7823   0.0239
  -6.500   0.1852   0.05145   0.04840  -0.1094   0.7767   0.0242
  -6.250   0.1939   0.04861   0.04556  -0.1119   0.7711   0.0245
  -6.000   0.2067   0.04536   0.04228  -0.1163   0.7656   0.0250
  -5.750   0.2277   0.04096   0.03775  -0.1262   0.7607   0.0253
  -5.500   0.2495   0.03689   0.03357  -0.1321   0.7560   0.0254
  -5.250   0.2610   0.03432   0.03102  -0.1314   0.7502   0.0255
  -5.000   0.2768   0.03194   0.02860  -0.1321   0.7449   0.0256
  -4.750   0.2946   0.02962   0.02621  -0.1332   0.7397   0.0258
  -4.500   0.3142   0.02726   0.02382  -0.1349   0.7338   0.0261
  -4.250   0.3358   0.02492   0.02140  -0.1369   0.7283   0.0265
  -4.000   0.3664   0.03884   0.03501  -0.1473   0.7359   0.0266
  -3.750   0.3925   0.03670   0.03276  -0.1490   0.7299   0.0272
  -3.500   0.4210   0.03450   0.03038  -0.1508   0.7242   0.0281
  -3.250   0.4602   0.03121   0.02668  -0.1532   0.7187   0.0289
  -3.000   0.4814   0.02935   0.02482  -0.1536   0.7120   0.0291
  -2.750   0.5050   0.02792   0.02330  -0.1541   0.7056   0.0294
  -2.500   0.5296   0.02651   0.02184  -0.1545   0.6986   0.0299
  -2.250   0.5560   0.02511   0.02030  -0.1548   0.6914   0.0307
  -2.000   0.5895   0.02314   0.01784  -0.1548   0.6845   0.0330
  -1.750   0.6132   0.02170   0.01640  -0.1550   0.6755   0.0333
  -1.500   0.6383   0.02069   0.01532  -0.1551   0.6665   0.0339
  -1.250   0.6642   0.01975   0.01425  -0.1550   0.6562   0.0350
  -1.000   0.6930   0.01860   0.01276  -0.1545   0.6449   0.0378
  -0.750   0.7175   0.01775   0.01186  -0.1544   0.6309   0.0386
  -0.500   0.7425   0.01711   0.01107  -0.1539   0.6136   0.0402
  -0.250   0.7680   0.01641   0.01005  -0.1531   0.5940   0.0433
   0.000   0.7911   0.01592   0.00943  -0.1524   0.5744   0.0447
   0.250   0.8155   0.01559   0.00882  -0.1515   0.5573   0.0494
   0.500   0.8390   0.01521   0.00836  -0.1510   0.5426   0.0518
   0.750   0.8634   0.01492   0.00791  -0.1504   0.5301   0.0579
   1.000   0.8872   0.01474   0.00758  -0.1497   0.5190   0.0659
   1.250   0.9122   0.01449   0.00728  -0.1494   0.5092   0.0761
   1.500   0.9363   0.01427   0.00700  -0.1489   0.5007   0.0891
   2.250   1.0148   0.01367   0.00598  -0.1466   0.4784   0.0636
   2.500   1.0403   0.01322   0.00544  -0.1458   0.4714   0.0477
   2.750   1.0652   0.01302   0.00522  -0.1453   0.4651   0.0445
   3.000   1.0907   0.01301   0.00518  -0.1448   0.4587   0.0429
   3.250   1.1149   0.01306   0.00519  -0.1442   0.4527   0.0427
   3.500   1.1400   0.01306   0.00520  -0.1438   0.4471   0.0431
   3.750   1.1650   0.01309   0.00524  -0.1434   0.4412   0.0445
   4.000   1.1885   0.01323   0.00535  -0.1427   0.4354   0.0467
   4.250   1.2127   0.01337   0.00547  -0.1421   0.4300   0.0477
   4.500   1.2370   0.01348   0.00558  -0.1415   0.4246   0.0497
   4.750   1.2599   0.01367   0.00574  -0.1408   0.4196   0.0549
   5.000   1.2796   0.01253   0.00625  -0.1397   0.4150   1.0000
   5.250   1.3030   0.01270   0.00642  -0.1389   0.4104   1.0000
   5.500   1.3244   0.01294   0.00660  -0.1379   0.4052   1.0000
   5.750   1.3444   0.01327   0.00685  -0.1366   0.3998   1.0000
   6.000   1.3665   0.01349   0.00708  -0.1357   0.3950   1.0000
   6.250   1.3882   0.01374   0.00732  -0.1348   0.3902   1.0000
   6.500   1.4088   0.01405   0.00760  -0.1337   0.3858   1.0000
   6.750   1.4292   0.01442   0.00792  -0.1326   0.3813   1.0000
   7.000   1.4508   0.01465   0.00821  -0.1318   0.3770   1.0000
   7.250   1.4713   0.01496   0.00851  -0.1307   0.3724   1.0000
   7.500   1.4904   0.01535   0.00886  -0.1295   0.3678   1.0000
   7.750   1.5106   0.01571   0.00924  -0.1285   0.3637   1.0000
   8.000   1.5314   0.01602   0.00959  -0.1276   0.3599   1.0000
   8.250   1.5513   0.01638   0.00996  -0.1266   0.3561   1.0000
   8.500   1.5697   0.01682   0.01039  -0.1254   0.3522   1.0000
   8.750   1.5885   0.01728   0.01085  -0.1243   0.3482   1.0000
   9.000   1.6083   0.01764   0.01128  -0.1233   0.3446   1.0000
   9.250   1.6268   0.01806   0.01173  -0.1222   0.3404   1.0000
   9.500   1.6434   0.01860   0.01225  -0.1209   0.3359   1.0000
   9.750   1.6603   0.01913   0.01282  -0.1196   0.3313   1.0000
  10.000   1.6780   0.01960   0.01335  -0.1186   0.3260   1.0000
  10.250   1.6932   0.02022   0.01397  -0.1171   0.3208   1.0000
  10.500   1.7083   0.02089   0.01464  -0.1158   0.3162   1.0000
  10.750   1.7257   0.02142   0.01527  -0.1148   0.3115   1.0000
  11.000   1.7409   0.02210   0.01597  -0.1135   0.3065   1.0000
  11.500   1.7698   0.02357   0.01752  -0.1109   0.2964   1.0000
  11.750   1.7822   0.02445   0.01843  -0.1095   0.2900   1.0000
  12.000   1.7941   0.02540   0.01940  -0.1080   0.2841   1.0000
  12.250   1.8079   0.02624   0.02031  -0.1069   0.2779   1.0000
  12.500   1.8173   0.02739   0.02146  -0.1053   0.2720   1.0000
  12.750   1.8301   0.02834   0.02249  -0.1041   0.2658   1.0000
  13.000   1.8377   0.02969   0.02384  -0.1026   0.2577   1.0000
  13.250   1.8471   0.03095   0.02515  -0.1012   0.2487   1.0000
  13.500   1.8518   0.03261   0.02682  -0.0996   0.2391   1.0000
  13.750   1.8556   0.03442   0.02862  -0.0980   0.2279   1.0000
  14.000   1.8579   0.03641   0.03061  -0.0964   0.2153   1.0000
  14.250   1.8559   0.03884   0.03302  -0.0946   0.2010   1.0000
  14.500   1.8488   0.04181   0.03594  -0.0927   0.1852   1.0000
  14.750   1.8391   0.04512   0.03921  -0.0908   0.1685   1.0000
  15.000   1.8271   0.04880   0.04285  -0.0890   0.1537   1.0000
  15.250   1.8150   0.05261   0.04665  -0.0875   0.1426   1.0000
  15.500   1.8032   0.05652   0.05057  -0.0862   0.1339   1.0000
  15.750   1.7948   0.06019   0.05428  -0.0852   0.1276   1.0000
  16.000   1.7822   0.06446   0.05859  -0.0843   0.1215   1.0000
  16.250   1.7739   0.06832   0.06253  -0.0838   0.1166   1.0000
  16.500   1.7641   0.07247   0.06674  -0.0833   0.1121   1.0000
  16.750   1.7504   0.07721   0.07154  -0.0831   0.1081   1.0000
  17.000   1.7449   0.08096   0.07538  -0.0830   0.1039   1.0000
  17.250   1.7336   0.08548   0.07997  -0.0830   0.0996   1.0000
  17.500   1.7191   0.09051   0.08506  -0.0832   0.0957   1.0000
  17.750   1.7124   0.09452   0.08915  -0.0834   0.0904   1.0000
  18.000   1.6966   0.09985   0.09451  -0.0839   0.0851   1.0000
  18.250   1.6863   0.10443   0.09915  -0.0845   0.0784   1.0000
  18.500   1.6715   0.10969   0.10444  -0.0853   0.0718   1.0000
  18.750   1.6544   0.11538   0.11014  -0.0863   0.0638   1.0000
  19.000   1.6357   0.12138   0.11613  -0.0876   0.0549   1.0000
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