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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 200,000
Max Cl/Cd: 86.38 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe484-il-200000-n5.txt
Download as CSV file: xf-goe484-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2498   0.09121   0.08778  -0.0395   0.9915   0.0303
  -8.500  -0.2401   0.08753   0.08411  -0.0417   0.9891   0.0312
  -8.250  -0.3517   0.09922   0.09566  -0.0316   0.9974   0.0290
  -8.000  -0.3367   0.09596   0.09240  -0.0340   0.9949   0.0298
  -7.750  -0.3232   0.09275   0.08918  -0.0370   0.9914   0.0306
  -7.500  -0.3086   0.08948   0.08591  -0.0406   0.9874   0.0317
  -7.250  -0.2961   0.08628   0.08271  -0.0444   0.9820   0.0334
  -7.000  -0.2689   0.08149   0.07789  -0.0594   0.9734   0.0358
  -6.750  -0.2409   0.07661   0.07296  -0.0691   0.9684   0.0361
  -6.500  -0.2303   0.07218   0.06854  -0.0686   0.9653   0.0370
  -6.250  -0.2118   0.06925   0.06559  -0.0702   0.9600   0.0379
  -6.000  -0.1846   0.06585   0.06215  -0.0749   0.9569   0.0392
  -5.750  -0.1625   0.06254   0.05880  -0.0793   0.9504   0.0409
  -5.500  -0.1053   0.05445   0.05048  -0.0997   0.9459   0.0465
  -5.250  -0.0893   0.05197   0.04801  -0.0996   0.9409   0.0474
  -5.000  -0.0640   0.04928   0.04526  -0.1020   0.9367   0.0486
  -4.750  -0.0297   0.04594   0.04182  -0.1072   0.9341   0.0502
  -4.500   0.0052   0.04196   0.03769  -0.1129   0.9298   0.0510
  -4.250   0.0604   0.02942   0.02413  -0.1254   0.9244   0.0360
  -4.000   0.0941   0.02572   0.02009  -0.1286   0.9215   0.0356
  -3.750   0.1290   0.02279   0.01671  -0.1314   0.9195   0.0355
  -3.500   0.1535   0.02099   0.01455  -0.1313   0.9134   0.0355
  -3.250   0.1847   0.01978   0.01300  -0.1322   0.9097   0.0361
  -3.000   0.2170   0.01779   0.01067  -0.1337   0.9070   0.0370
  -2.750   0.2472   0.01676   0.00941  -0.1342   0.9033   0.0370
  -2.500   0.2737   0.01596   0.00843  -0.1340   0.8978   0.0370
  -2.250   0.3046   0.01512   0.00746  -0.1346   0.8941   0.0372
  -2.000   0.3374   0.01437   0.00661  -0.1355   0.8911   0.0376
  -1.750   0.3632   0.01384   0.00604  -0.1350   0.8847   0.0380
  -1.500   0.3928   0.01332   0.00549  -0.1352   0.8796   0.0386
  -1.250   0.4253   0.01284   0.00498  -0.1361   0.8758   0.0393
  -1.000   0.4514   0.01254   0.00468  -0.1356   0.8689   0.0401
  -0.750   0.4811   0.01223   0.00437  -0.1358   0.8633   0.0417
  -0.500   0.5116   0.01196   0.00409  -0.1362   0.8578   0.0440
  -0.250   0.5388   0.01177   0.00389  -0.1359   0.8500   0.0451
   0.000   0.5703   0.01155   0.00363  -0.1364   0.8441   0.0461
   0.250   0.5964   0.01140   0.00351  -0.1359   0.8352   0.0484
   0.500   0.6269   0.01123   0.00336  -0.1362   0.8286   0.0527
   0.750   0.6531   0.01107   0.00336  -0.1357   0.8190   0.0830
   1.000   0.6814   0.01092   0.00338  -0.1357   0.8102   0.1470
   1.250   0.7091   0.01080   0.00339  -0.1355   0.8001   0.1922
   1.500   0.7339   0.01019   0.00355  -0.1351   0.7873   0.4694
   2.000   0.7905   0.00929   0.00338  -0.1343   0.7334   1.0000
   2.250   0.8146   0.00943   0.00322  -0.1330   0.6827   1.0000
   2.500   0.8376   0.00973   0.00321  -0.1316   0.6389   1.0000
   2.750   0.8610   0.01005   0.00334  -0.1304   0.6108   1.0000
   3.000   0.8838   0.01039   0.00351  -0.1292   0.5823   1.0000
   3.250   0.9058   0.01076   0.00371  -0.1279   0.5488   1.0000
   3.500   0.9275   0.01113   0.00394  -0.1265   0.5133   1.0000
   3.750   0.9460   0.01166   0.00420  -0.1246   0.4493   1.0000
   4.000   0.9520   0.01316   0.00478  -0.1208   0.2877   1.0000
   4.250   0.9583   0.01506   0.00569  -0.1174   0.1123   1.0000
   4.500   0.9755   0.01603   0.00636  -0.1156   0.0670   1.0000
   4.750   0.9971   0.01656   0.00689  -0.1145   0.0600   1.0000
   5.000   1.0191   0.01702   0.00740  -0.1134   0.0564   1.0000
   5.250   1.0403   0.01756   0.00797  -0.1121   0.0535   1.0000
   5.500   1.0604   0.01818   0.00864  -0.1107   0.0511   1.0000
   5.750   1.0785   0.01895   0.00946  -0.1090   0.0487   1.0000
   6.000   1.0986   0.01951   0.01009  -0.1077   0.0472   1.0000
   6.250   1.1176   0.02016   0.01082  -0.1061   0.0457   1.0000
   6.500   1.1355   0.02089   0.01161  -0.1044   0.0444   1.0000
   6.750   1.1533   0.02165   0.01242  -0.1027   0.0427   1.0000
   7.000   1.1708   0.02242   0.01325  -0.1010   0.0408   1.0000
   7.250   1.1870   0.02336   0.01420  -0.0992   0.0392   1.0000
   7.500   1.2012   0.02482   0.01567  -0.0972   0.0375   1.0000
   7.750   1.2197   0.02558   0.01651  -0.0956   0.0363   1.0000
   8.000   1.2379   0.02634   0.01741  -0.0941   0.0345   1.0000
   8.250   1.2561   0.02729   0.01845  -0.0926   0.0329   1.0000
   8.500   1.2732   0.02816   0.01939  -0.0910   0.0311   1.0000
   8.750   1.2892   0.02907   0.02032  -0.0894   0.0296   1.0000
   9.000   1.3083   0.03076   0.02204  -0.0885   0.0279   1.0000
   9.250   1.3261   0.03179   0.02330  -0.0869   0.0267   1.0000
   9.500   1.3427   0.03289   0.02458  -0.0853   0.0249   1.0000
   9.750   1.3567   0.03385   0.02567  -0.0834   0.0235   1.0000
  10.000   1.3689   0.03478   0.02667  -0.0814   0.0224   1.0000
  10.250   1.3809   0.03597   0.02791  -0.0795   0.0216   1.0000
  10.500   1.3951   0.03783   0.02997  -0.0780   0.0206   1.0000
  10.750   1.4082   0.03978   0.03227  -0.0761   0.0194   1.0000
  11.000   1.4175   0.04155   0.03428  -0.0740   0.0182   1.0000
  11.250   1.4240   0.04294   0.03585  -0.0716   0.0174   1.0000
  11.500   1.4293   0.04427   0.03730  -0.0693   0.0168   1.0000
  11.750   1.4337   0.04573   0.03888  -0.0672   0.0164   1.0000
  12.000   1.4368   0.04752   0.04079  -0.0651   0.0160   1.0000
  12.250   1.4366   0.05006   0.04352  -0.0630   0.0156   1.0000
  12.500   1.4310   0.05393   0.04781  -0.0607   0.0153   1.0000
  12.750   1.4194   0.05837   0.05266  -0.0585   0.0148   1.0000
  13.000   1.4045   0.06306   0.05771  -0.0568   0.0145   1.0000
  13.250   1.3870   0.06812   0.06310  -0.0558   0.0143   1.0000
  13.500   1.3669   0.07370   0.06897  -0.0556   0.0141   1.0000
  13.750   1.3450   0.07989   0.07544  -0.0564   0.0140   1.0000
  14.000   1.3204   0.08699   0.08280  -0.0585   0.0139   1.0000
  14.250   1.2937   0.09515   0.09121  -0.0620   0.0140   1.0000
  14.500   1.2642   0.10475   0.10104  -0.0671   0.0141   1.0000
  14.750   1.2333   0.11596   0.11246  -0.0740   0.0144   1.0000
  15.000   1.2012   0.12949   0.12616  -0.0832   0.0148   1.0000
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