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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 100,000
Max Cl/Cd: 69.21 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe495-il-100000.txt
Download as CSV file: xf-goe495-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 495 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3489   0.09993   0.09521  -0.0309   1.0000   0.0822
  -7.500  -0.3696   0.10012   0.09555  -0.0290   1.0000   0.0828
  -7.250  -0.3835   0.09967   0.09522  -0.0303   1.0000   0.0832
  -7.000  -0.3913   0.09810   0.09376  -0.0332   1.0000   0.0836
  -6.750  -0.3770   0.09187   0.08750  -0.0231   1.0000   0.0864
  -6.500  -0.3787   0.08985   0.08553  -0.0209   1.0000   0.0885
  -6.250  -0.3827   0.08797   0.08371  -0.0198   1.0000   0.0910
  -6.000  -0.3865   0.08607   0.08186  -0.0208   1.0000   0.0944
  -5.750  -0.3778   0.08341   0.07920  -0.0358   1.0000   0.0976
  -5.500  -0.3817   0.08009   0.07596  -0.0275   1.0000   0.0990
  -5.250  -0.3794   0.07770   0.07360  -0.0238   1.0000   0.1016
  -5.000  -0.3434   0.07335   0.06907  -0.0431   1.0000   0.1116
  -4.750  -0.3495   0.07045   0.06630  -0.0350   1.0000   0.1130
  -4.500  -0.3469   0.06854   0.06441  -0.0306   1.0000   0.1174
  -4.250  -0.3184   0.06401   0.05978  -0.0397   1.0000   0.1278
  -4.000  -0.3090   0.06170   0.05748  -0.0379   1.0000   0.1323
  -3.750  -0.2491   0.05692   0.05223  -0.0558   1.0000   0.1545
  -3.500  -0.2431   0.05341   0.04889  -0.0525   1.0000   0.1565
  -3.250  -0.2035   0.04992   0.04530  -0.0577   0.9956   0.1724
  -3.000  -0.0944   0.03329   0.02698  -0.0821   0.9976   0.0942
  -2.750  -0.0429   0.02889   0.02178  -0.0880   0.9949   0.0915
  -2.500   0.0031   0.02619   0.01836  -0.0919   0.9909   0.0928
  -2.250   0.0470   0.02454   0.01605  -0.0949   0.9864   0.0964
  -2.000   0.0875   0.02348   0.01485  -0.0977   0.9816   0.1041
  -1.750   0.1266   0.02264   0.01366  -0.0998   0.9754   0.1111
  -1.500   0.1690   0.02202   0.01308  -0.1028   0.9709   0.1274
  -1.250   0.2032   0.02144   0.01258  -0.1042   0.9633   0.1550
  -1.000   0.2451   0.02072   0.01230  -0.1072   0.9581   0.2585
  -0.750   0.2777   0.02064   0.01248  -0.1086   0.9498   0.3366
  -0.500   0.3196   0.02051   0.01270  -0.1115   0.9440   0.4487
  -0.250   0.3509   0.02002   0.01275  -0.1122   0.9359   0.5976
   0.000   0.3921   0.01924   0.01247  -0.1144   0.9300   1.0000
   0.500   0.4666   0.01974   0.01256  -0.1183   0.9135   1.0000
   0.750   0.4998   0.01998   0.01267  -0.1195   0.9039   1.0000
   1.000   0.5338   0.02021   0.01280  -0.1207   0.8946   1.0000
   1.250   0.5773   0.02024   0.01278  -0.1235   0.8879   1.0000
   1.500   0.6084   0.02044   0.01293  -0.1241   0.8773   1.0000
   1.750   0.6592   0.02019   0.01267  -0.1279   0.8725   1.0000
   2.000   0.6898   0.02029   0.01277  -0.1283   0.8609   1.0000
   2.250   0.7241   0.02031   0.01283  -0.1291   0.8509   1.0000
   2.500   0.7688   0.01996   0.01253  -0.1315   0.8448   1.0000
   2.750   0.7983   0.02004   0.01266  -0.1314   0.8334   1.0000
   3.000   0.8325   0.01986   0.01258  -0.1318   0.8227   1.0000
   3.250   0.8768   0.01917   0.01197  -0.1334   0.8149   1.0000
   3.500   0.9075   0.01893   0.01180  -0.1329   0.8015   1.0000
   3.750   0.9376   0.01870   0.01170  -0.1323   0.7878   1.0000
   4.000   0.9679   0.01842   0.01152  -0.1316   0.7735   1.0000
   4.250   0.9980   0.01810   0.01130  -0.1307   0.7584   1.0000
   4.500   1.0278   0.01780   0.01110  -0.1299   0.7427   1.0000
   4.750   1.0515   0.01754   0.01098  -0.1279   0.7199   1.0000
   5.000   1.0776   0.01683   0.01029  -0.1255   0.6888   1.0000
   5.250   1.1002   0.01641   0.00985  -0.1229   0.6499   1.0000
   5.500   1.1221   0.01633   0.00974  -0.1205   0.6084   1.0000
   5.750   1.1426   0.01651   0.00992  -0.1182   0.5632   1.0000
   6.000   1.1586   0.01696   0.01016  -0.1151   0.4936   1.0000
   6.250   1.1627   0.01830   0.01067  -0.1104   0.3454   1.0000
   6.500   1.1531   0.02169   0.01254  -0.1048   0.1663   1.0000
   6.750   1.1587   0.02404   0.01440  -0.1013   0.1173   1.0000
   7.000   1.1712   0.02571   0.01594  -0.0987   0.0987   1.0000
   7.250   1.1858   0.02743   0.01760  -0.0965   0.0864   1.0000
   7.500   1.2041   0.02949   0.01949  -0.0951   0.0768   1.0000
   7.750   1.2286   0.03134   0.02151  -0.0941   0.0700   1.0000
   8.000   1.2560   0.03410   0.02414  -0.0941   0.0631   1.0000
   8.250   1.2842   0.03655   0.02692  -0.0934   0.0599   1.0000
   8.500   1.3094   0.03917   0.02979  -0.0927   0.0566   1.0000
   8.750   1.3329   0.04270   0.03338  -0.0925   0.0526   1.0000
   9.000   1.3517   0.04715   0.03826  -0.0911   0.0517   1.0000
   9.250   1.3653   0.05112   0.04272  -0.0890   0.0517   1.0000
   9.500   1.3775   0.05627   0.04830  -0.0872   0.0521   1.0000
   9.750   1.3847   0.05965   0.05213  -0.0845   0.0524   1.0000
  10.000   1.3869   0.06383   0.05674  -0.0817   0.0525   1.0000
  10.250   1.3848   0.06782   0.06114  -0.0787   0.0526   1.0000
  10.500   1.3408   0.07250   0.06686  -0.0711   0.0580   1.0000
  10.750   1.3197   0.07687   0.07150  -0.0675   0.0594   1.0000
  11.000   1.2991   0.08135   0.07619  -0.0649   0.0606   1.0000
  11.250   1.2807   0.08629   0.08130  -0.0635   0.0617   1.0000
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