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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 100,000
Max Cl/Cd: 57.42 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe492-il-100000-n5.txt
Download as CSV file: xf-goe492-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4029   0.10145   0.09657  -0.0341   1.0000   0.0379
  -8.250  -0.4040   0.09874   0.09393  -0.0346   1.0000   0.0380
  -8.000  -0.4070   0.09596   0.09123  -0.0347   1.0000   0.0380
  -7.500  -0.4016   0.08788   0.08320  -0.0311   1.0000   0.0264
  -7.250  -0.4077   0.08541   0.08083  -0.0301   1.0000   0.0253
  -7.000  -0.4115   0.08248   0.07798  -0.0302   1.0000   0.0242
  -6.750  -0.4145   0.07944   0.07501  -0.0307   1.0000   0.0233
  -6.500  -0.4163   0.07601   0.07165  -0.0320   1.0000   0.0223
  -6.250  -0.4157   0.07197   0.06765  -0.0343   1.0000   0.0214
  -6.000  -0.4090   0.06577   0.06143  -0.0399   1.0000   0.0198
  -5.500  -0.3828   0.05593   0.05139  -0.0463   1.0000   0.0187
  -5.250  -0.3657   0.05033   0.04563  -0.0499   0.9996   0.0185
  -5.000  -0.3290   0.04291   0.03781  -0.0577   0.9957   0.0184
  -4.500  -0.2592   0.03261   0.02650  -0.0678   0.9884   0.0216
  -4.250  -0.2239   0.02843   0.02156  -0.0708   0.9851   0.0228
  -4.000  -0.1893   0.02490   0.01727  -0.0726   0.9818   0.0244
  -3.750  -0.1535   0.02231   0.01384  -0.0740   0.9791   0.0291
  -3.500  -0.1213   0.02078   0.01211  -0.0752   0.9754   0.0347
  -3.250  -0.0888   0.01956   0.01062  -0.0762   0.9712   0.0461
  -3.000  -0.0543   0.01855   0.00933  -0.0778   0.9678   0.0621
  -2.750  -0.0240   0.01775   0.00844  -0.0786   0.9628   0.0747
  -2.500   0.0087   0.01705   0.00763  -0.0797   0.9581   0.0819
  -2.250   0.0446   0.01656   0.00699  -0.0814   0.9546   0.0908
  -2.000   0.0733   0.01610   0.00646  -0.0818   0.9480   0.1055
  -1.750   0.1072   0.01538   0.00624  -0.0834   0.9436   0.2040
  -1.500   0.1407   0.01524   0.00612  -0.0847   0.9386   0.2922
  -1.250   0.1719   0.01502   0.00589  -0.0856   0.9321   0.3353
  -1.000   0.2081   0.01443   0.00575  -0.0876   0.9284   0.4325
  -0.750   0.2447   0.01303   0.00569  -0.0888   0.9246   1.0000
  -0.500   0.2780   0.01306   0.00551  -0.0899   0.9177   1.0000
  -0.250   0.3135   0.01307   0.00536  -0.0914   0.9120   1.0000
   0.000   0.3447   0.01310   0.00527  -0.0921   0.9038   1.0000
   0.250   0.3778   0.01310   0.00520  -0.0931   0.8966   1.0000
   0.500   0.4103   0.01310   0.00513  -0.0939   0.8886   1.0000
   0.750   0.4402   0.01312   0.00511  -0.0943   0.8793   1.0000
   1.000   0.4752   0.01307   0.00506  -0.0955   0.8724   1.0000
   1.250   0.5028   0.01312   0.00512  -0.0953   0.8615   1.0000
   1.500   0.5315   0.01316   0.00518  -0.0954   0.8510   1.0000
   1.750   0.5613   0.01317   0.00525  -0.0956   0.8411   1.0000
   2.000   0.5924   0.01317   0.00535  -0.0960   0.8318   1.0000
   2.250   0.6197   0.01323   0.00550  -0.0957   0.8195   1.0000
   2.500   0.6478   0.01326   0.00563  -0.0954   0.8060   1.0000
   2.750   0.6762   0.01326   0.00579  -0.0951   0.7909   1.0000
   3.000   0.7042   0.01328   0.00595  -0.0948   0.7750   1.0000
   3.250   0.7309   0.01336   0.00622  -0.0942   0.7577   1.0000
   3.500   0.7574   0.01331   0.00630  -0.0931   0.7277   1.0000
   3.750   0.7746   0.01349   0.00568  -0.0885   0.5700   1.0000
   4.000   0.7730   0.01614   0.00627  -0.0832   0.1963   1.0000
   4.250   0.7826   0.01864   0.00779  -0.0804   0.0396   1.0000
   4.500   0.8021   0.01974   0.00905  -0.0787   0.0314   1.0000
   4.750   0.8203   0.02089   0.01032  -0.0770   0.0255   1.0000
   5.000   0.8379   0.02215   0.01177  -0.0750   0.0232   1.0000
   5.250   0.8554   0.02362   0.01341  -0.0730   0.0215   1.0000
   5.500   0.8748   0.02528   0.01509  -0.0715   0.0190   1.0000
   5.750   0.8980   0.02769   0.01755  -0.0706   0.0172   1.0000
   6.000   0.9251   0.02997   0.02007  -0.0698   0.0167   1.0000
   6.250   0.9517   0.03260   0.02300  -0.0689   0.0164   1.0000
   6.500   0.9760   0.03548   0.02626  -0.0677   0.0163   1.0000
   6.750   0.9972   0.03855   0.02977  -0.0661   0.0162   1.0000
   7.000   1.0155   0.04156   0.03325  -0.0642   0.0157   1.0000
   7.250   1.0308   0.04471   0.03688  -0.0620   0.0150   1.0000
   7.500   1.0431   0.04815   0.04086  -0.0596   0.0146   1.0000
   7.750   1.0520   0.05188   0.04500  -0.0572   0.0148   1.0000
   8.000   1.0576   0.05575   0.04925  -0.0547   0.0151   1.0000
   8.250   1.0598   0.05974   0.05358  -0.0522   0.0154   1.0000
   8.500   1.0588   0.06370   0.05783  -0.0497   0.0157   1.0000
   8.750   1.0544   0.06768   0.06207  -0.0474   0.0161   1.0000
   9.000   1.0468   0.07156   0.06616  -0.0451   0.0164   1.0000
   9.250   1.0348   0.07521   0.06998  -0.0427   0.0166   1.0000
   9.500   1.0197   0.07893   0.07384  -0.0406   0.0168   1.0000
   9.750   1.0040   0.08297   0.07800  -0.0397   0.0170   1.0000
  10.250   0.8574   0.08759   0.08329  -0.0360   0.0164   1.0000
  10.500   0.8363   0.09408   0.08988  -0.0391   0.0164   1.0000
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