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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 200,000
Max Cl/Cd: 82.05 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe359-il-200000-n5.txt
Download as CSV file: xf-goe359-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2748   0.11603   0.11261  -0.0303   1.0000   0.0180
  -9.000  -0.2710   0.11324   0.10987  -0.0310   1.0000   0.0180
  -8.750  -0.2677   0.11047   0.10715  -0.0315   1.0000   0.0180
  -8.500  -0.1712   0.09035   0.08739  -0.0370   0.9932   0.0186
  -8.250  -0.1543   0.08615   0.08318  -0.0383   0.9854   0.0199
  -8.000  -0.1422   0.08238   0.07941  -0.0408   0.9733   0.0210
  -7.750  -0.1311   0.07847   0.07550  -0.0435   0.9561   0.0218
  -7.500  -0.1177   0.07429   0.07129  -0.0469   0.9390   0.0227
  -7.250  -0.2275   0.09006   0.08699  -0.0347   0.9843   0.0196
  -7.000  -0.2086   0.08646   0.08338  -0.0388   0.9662   0.0205
  -6.750  -0.1869   0.08244   0.07935  -0.0443   0.9441   0.0211
  -6.500  -0.1480   0.07602   0.07284  -0.0598   0.9234   0.0178
  -6.250  -0.1250   0.07149   0.06825  -0.0631   0.9104   0.0172
  -6.000  -0.0967   0.06693   0.06360  -0.0697   0.8946   0.0170
  -5.750  -0.0674   0.06229   0.05885  -0.0769   0.8782   0.0171
  -5.500  -0.0399   0.05841   0.05488  -0.0827   0.8626   0.0193
  -5.250  -0.0174   0.05622   0.05260  -0.0850   0.8481   0.0213
  -5.000   0.0128   0.05162   0.04785  -0.0911   0.8347   0.0206
  -4.750   0.0433   0.04748   0.04354  -0.0963   0.8222   0.0207
  -4.500   0.0738   0.04382   0.03971  -0.1005   0.8096   0.0217
  -4.250   0.1076   0.04004   0.03568  -0.1049   0.7976   0.0244
  -4.000   0.1435   0.03528   0.03060  -0.1093   0.7866   0.0253
  -3.750   0.1776   0.03064   0.02556  -0.1127   0.7763   0.0282
  -3.500   0.1998   0.03033   0.02520  -0.1127   0.7641   0.0309
  -3.250   0.2307   0.02719   0.02171  -0.1143   0.7527   0.0321
  -3.000   0.2611   0.02446   0.01855  -0.1153   0.7415   0.0345
  -2.750   0.2915   0.02193   0.01549  -0.1158   0.7305   0.0365
  -2.500   0.3203   0.02019   0.01329  -0.1160   0.7192   0.0372
  -2.250   0.3487   0.01917   0.01183  -0.1159   0.7077   0.0390
  -2.000   0.3759   0.01764   0.01000  -0.1160   0.6968   0.0400
  -1.750   0.4035   0.01676   0.00880  -0.1158   0.6856   0.0398
  -1.250   0.4580   0.01526   0.00685  -0.1154   0.6630   0.0406
  -1.000   0.4851   0.01470   0.00613  -0.1151   0.6522   0.0414
  -0.750   0.5121   0.01427   0.00556  -0.1149   0.6420   0.0423
  -0.500   0.5389   0.01393   0.00510  -0.1145   0.6311   0.0431
  -0.250   0.5657   0.01366   0.00475  -0.1143   0.6196   0.0447
   0.000   0.5923   0.01348   0.00449  -0.1140   0.6078   0.0472
   0.250   0.6189   0.01329   0.00422  -0.1136   0.5960   0.0478
   0.500   0.6454   0.01314   0.00399  -0.1133   0.5850   0.0478
   0.750   0.6722   0.01301   0.00382  -0.1130   0.5740   0.0479
   1.000   0.6989   0.01294   0.00370  -0.1128   0.5637   0.0482
   1.250   0.7255   0.01291   0.00360  -0.1125   0.5537   0.0486
   1.500   0.7522   0.01291   0.00353  -0.1122   0.5435   0.0493
   1.750   0.7789   0.01293   0.00350  -0.1119   0.5338   0.0503
   2.000   0.8053   0.01296   0.00347  -0.1116   0.5236   0.0526
   2.250   0.8316   0.01299   0.00347  -0.1113   0.5129   0.0592
   2.500   0.8577   0.01268   0.00367  -0.1112   0.5031   0.2789
   3.000   0.9083   0.01172   0.00389  -0.1101   0.4849   1.0000
   3.250   0.9341   0.01192   0.00401  -0.1098   0.4739   1.0000
   3.500   0.9597   0.01213   0.00416  -0.1094   0.4623   1.0000
   3.750   0.9851   0.01235   0.00431  -0.1089   0.4509   1.0000
   4.000   1.0107   0.01257   0.00449  -0.1085   0.4402   1.0000
   4.250   1.0363   0.01278   0.00468  -0.1082   0.4303   1.0000
   4.500   1.0614   0.01302   0.00491  -0.1077   0.4196   1.0000
   4.750   1.0863   0.01327   0.00514  -0.1073   0.4082   1.0000
   5.000   1.1109   0.01354   0.00538  -0.1067   0.3932   1.0000
   5.250   1.1337   0.01388   0.00564  -0.1060   0.3629   1.0000
   5.500   1.1540   0.01444   0.00594  -0.1049   0.3110   1.0000
   5.750   1.1713   0.01533   0.00645  -0.1034   0.2555   1.0000
   6.000   1.1890   0.01626   0.00709  -0.1021   0.2162   1.0000
   6.250   1.2089   0.01697   0.00768  -0.1010   0.1866   1.0000
   6.500   1.2202   0.01849   0.00864  -0.0990   0.1090   1.0000
   6.750   1.2323   0.01992   0.00974  -0.0969   0.0544   1.0000
   7.000   1.2515   0.02062   0.01046  -0.0957   0.0429   1.0000
   7.250   1.2669   0.02166   0.01143  -0.0940   0.0175   1.0000
   7.500   1.2852   0.02239   0.01230  -0.0926   0.0155   1.0000
   7.750   1.3027   0.02315   0.01323  -0.0911   0.0143   1.0000
   8.000   1.3183   0.02404   0.01429  -0.0893   0.0130   1.0000
   8.250   1.3334   0.02489   0.01529  -0.0876   0.0120   1.0000
   8.500   1.3454   0.02584   0.01640  -0.0853   0.0115   1.0000
   8.750   1.3551   0.02691   0.01762  -0.0829   0.0110   1.0000
   9.000   1.3627   0.02814   0.01901  -0.0803   0.0106   1.0000
   9.250   1.3682   0.02956   0.02059  -0.0778   0.0103   1.0000
   9.500   1.3712   0.03124   0.02246  -0.0753   0.0100   1.0000
   9.750   1.3714   0.03326   0.02463  -0.0730   0.0097   1.0000
  10.000   1.3676   0.03580   0.02732  -0.0710   0.0093   1.0000
  10.250   1.3592   0.03900   0.03064  -0.0692   0.0090   1.0000
  10.500   1.3476   0.04275   0.03449  -0.0678   0.0088   1.0000
  10.750   1.3543   0.04476   0.03662  -0.0671   0.0084   1.0000
  11.000   1.3546   0.04753   0.03951  -0.0664   0.0082   1.0000
  11.250   1.3531   0.05054   0.04263  -0.0658   0.0081   1.0000
  11.500   1.3516   0.05361   0.04581  -0.0652   0.0080   1.0000
  11.750   1.3504   0.05667   0.04896  -0.0646   0.0079   1.0000
  12.000   1.3497   0.05967   0.05205  -0.0640   0.0077   1.0000
  12.250   1.3499   0.06255   0.05502  -0.0633   0.0076   1.0000
  12.500   1.3511   0.06532   0.05786  -0.0625   0.0075   1.0000
  12.750   1.3532   0.06798   0.06061  -0.0617   0.0074   1.0000
  13.000   1.3563   0.07055   0.06327  -0.0608   0.0073   1.0000
  13.250   1.3603   0.07305   0.06591  -0.0599   0.0073   1.0000
  13.500   1.3647   0.07554   0.06850  -0.0589   0.0072   1.0000
  13.750   1.3685   0.07817   0.07125  -0.0582   0.0071   1.0000
  14.000   1.3713   0.08100   0.07419  -0.0577   0.0069   1.0000
  14.250   1.3745   0.08378   0.07706  -0.0572   0.0067   1.0000
  14.500   1.3839   0.08565   0.07891  -0.0558   0.0063   1.0000
  14.750   1.3957   0.08773   0.08101  -0.0535   0.0060   1.0000
  15.000   1.3828   0.09268   0.08622  -0.0554   0.0059   1.0000
  15.250   1.3746   0.09733   0.09110  -0.0569   0.0059   1.0000
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