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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 200,000
Max Cl/Cd: 83.38 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe81-il-200000-n5.txt
Download as CSV file: xf-goe81-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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  -0.2453   0.10961   0.10610  -0.0327   1.0000   0.0219
  -9.000  -0.2431   0.10736   0.10391  -0.0328   1.0000   0.0224
  -8.750  -0.2420   0.10530   0.10191  -0.0331   0.9992   0.0226
  -8.500  -0.2264   0.10216   0.09877  -0.0393   0.9886   0.0229
  -8.000  -0.1957   0.09430   0.09091  -0.0454   0.9686   0.0233
  -7.750  -0.1795   0.09078   0.08738  -0.0481   0.9579   0.0237
  -7.500  -0.1620   0.08740   0.08399  -0.0517   0.9466   0.0242
  -7.250  -0.1427   0.08398   0.08054  -0.0561   0.9358   0.0249
  -7.000  -0.1225   0.08058   0.07711  -0.0609   0.9247   0.0259
  -6.750  -0.0925   0.07742   0.07387  -0.0718   0.9116   0.0273
  -6.500  -0.0627   0.07390   0.07025  -0.0813   0.9005   0.0275
  -6.250  -0.0417   0.07010   0.06638  -0.0851   0.8912   0.0276
  -6.000  -0.0319   0.06682   0.06310  -0.0833   0.8823   0.0279
  -5.750  -0.0153   0.06394   0.06017  -0.0843   0.8733   0.0284
  -5.500   0.0041   0.06130   0.05748  -0.0865   0.8624   0.0294
  -5.250   0.0278   0.05854   0.05465  -0.0900   0.8513   0.0309
  -5.000   0.0633   0.05553   0.05149  -0.0968   0.8402   0.0328
  -4.750   0.1088   0.05253   0.04820  -0.1055   0.8291   0.0334
  -4.500   0.1333   0.04899   0.04456  -0.1080   0.8186   0.0337
  -4.250   0.1477   0.04622   0.04180  -0.1076   0.8089   0.0344
  -4.000   0.1693   0.04403   0.03954  -0.1085   0.7987   0.0356
  -3.750   0.1970   0.04175   0.03715  -0.1107   0.7882   0.0371
  -3.500   0.2284   0.03942   0.03464  -0.1134   0.7784   0.0389
  -3.250   0.2771   0.03771   0.03244  -0.1180   0.7683   0.0413
  -3.000   0.3019   0.03447   0.02911  -0.1195   0.7584   0.0420
  -2.750   0.3238   0.03246   0.02706  -0.1200   0.7484   0.0431
  -2.500   0.3497   0.03094   0.02543  -0.1208   0.7384   0.0453
  -2.250   0.3907   0.03024   0.02423  -0.1224   0.7302   0.0509
  -2.000   0.4175   0.02747   0.02135  -0.1236   0.7222   0.0518
  -1.750   0.4430   0.02585   0.01968  -0.1243   0.7141   0.0531
  -1.500   0.4706   0.02462   0.01832  -0.1248   0.7059   0.0553
  -1.250   0.5049   0.02378   0.01703  -0.1254   0.6983   0.0627
  -0.750   0.5586   0.02123   0.01436  -0.1263   0.6829   0.0681
  -0.250   0.6235   0.01786   0.01011  -0.1261   0.6682   0.0402
   0.000   0.6518   0.01697   0.00904  -0.1261   0.6596   0.0391
   0.250   0.6800   0.01624   0.00811  -0.1259   0.6501   0.0383
   0.750   0.7353   0.01514   0.00665  -0.1254   0.6291   0.0377
   1.000   0.7625   0.01476   0.00615  -0.1251   0.6185   0.0384
   1.500   0.8165   0.01425   0.00545  -0.1245   0.5970   0.0404
   1.750   0.8433   0.01399   0.00516  -0.1242   0.5855   0.0404
   2.000   0.8698   0.01379   0.00492  -0.1238   0.5729   0.0406
   2.250   0.8962   0.01364   0.00475  -0.1235   0.5583   0.0410
   2.500   0.9224   0.01355   0.00464  -0.1231   0.5417   0.0414
   2.750   0.9485   0.01344   0.00451  -0.1228   0.5226   0.0425
   3.000   0.9739   0.01347   0.00446  -0.1224   0.5014   0.0446
   3.250   0.9986   0.01361   0.00448  -0.1218   0.4796   0.0484
   3.500   1.0232   0.01380   0.00455  -0.1212   0.4612   0.0506
   3.750   1.0482   0.01399   0.00466  -0.1206   0.4475   0.0547
   4.000   1.0730   0.01420   0.00484  -0.1201   0.4358   0.0722
   4.250   1.0940   0.01312   0.00515  -0.1189   0.4241   1.0000
   4.500   1.1186   0.01344   0.00537  -0.1183   0.4118   1.0000
   4.750   1.1430   0.01377   0.00561  -0.1178   0.4003   1.0000
   5.000   1.1671   0.01413   0.00588  -0.1172   0.3896   1.0000
   5.250   1.1918   0.01442   0.00616  -0.1167   0.3782   1.0000
   5.500   1.2161   0.01474   0.00645  -0.1162   0.3674   1.0000
   5.750   1.2400   0.01508   0.00676  -0.1156   0.3572   1.0000
   6.000   1.2642   0.01539   0.00709  -0.1150   0.3462   1.0000
   6.250   1.2876   0.01573   0.00742  -0.1144   0.3333   1.0000
   6.500   1.3106   0.01610   0.00777  -0.1137   0.3196   1.0000
   6.750   1.3334   0.01648   0.00816  -0.1130   0.3070   1.0000
   7.000   1.3557   0.01688   0.00856  -0.1122   0.2945   1.0000
   7.250   1.3773   0.01731   0.00899  -0.1113   0.2814   1.0000
   7.500   1.3984   0.01778   0.00945  -0.1103   0.2673   1.0000
   7.750   1.4180   0.01833   0.00999  -0.1092   0.2496   1.0000
   8.000   1.4352   0.01905   0.01060  -0.1077   0.2246   1.0000
   8.250   1.4503   0.01989   0.01131  -0.1060   0.1973   1.0000
   8.500   1.4633   0.02086   0.01213  -0.1040   0.1676   1.0000
   8.750   1.4759   0.02183   0.01300  -0.1020   0.1476   1.0000
   9.000   1.4876   0.02275   0.01387  -0.0998   0.1358   1.0000
   9.250   1.4999   0.02354   0.01469  -0.0976   0.1281   1.0000
   9.500   1.5105   0.02448   0.01565  -0.0953   0.1214   1.0000
   9.750   1.5230   0.02532   0.01656  -0.0934   0.1147   1.0000
  10.000   1.5315   0.02645   0.01772  -0.0911   0.1064   1.0000
  10.250   1.5445   0.02730   0.01868  -0.0894   0.0990   1.0000
  10.500   1.5556   0.02833   0.01978  -0.0877   0.0886   1.0000
  10.750   1.5576   0.03010   0.02136  -0.0853   0.0640   1.0000
  11.000   1.5604   0.03189   0.02313  -0.0831   0.0558   1.0000
  11.250   1.5626   0.03381   0.02509  -0.0811   0.0496   1.0000
  11.500   1.5680   0.03552   0.02692  -0.0795   0.0416   1.0000
  11.750   1.5686   0.03774   0.02914  -0.0777   0.0257   1.0000
  12.000   1.5647   0.04049   0.03184  -0.0760   0.0209   1.0000
  12.250   1.5638   0.04306   0.03449  -0.0746   0.0191   1.0000
  12.500   1.5622   0.04581   0.03735  -0.0734   0.0179   1.0000
  12.750   1.5595   0.04877   0.04044  -0.0723   0.0169   1.0000
  13.000   1.5584   0.05165   0.04348  -0.0715   0.0162   1.0000
  13.250   1.5560   0.05476   0.04676  -0.0709   0.0156   1.0000
  13.500   1.5519   0.05814   0.05031  -0.0705   0.0150   1.0000
  13.750   1.5465   0.06180   0.05413  -0.0702   0.0145   1.0000
  14.000   1.5398   0.06578   0.05827  -0.0702   0.0141   1.0000
  14.250   1.5319   0.07005   0.06270  -0.0704   0.0139   1.0000
  14.500   1.5228   0.07463   0.06744  -0.0709   0.0136   1.0000
  14.750   1.5124   0.07957   0.07254  -0.0717   0.0134   1.0000
  15.000   1.5008   0.08482   0.07795  -0.0727   0.0132   1.0000
  15.250   1.4887   0.09032   0.08360  -0.0740   0.0130   1.0000
  15.500   1.4761   0.09604   0.08946  -0.0755   0.0129   1.0000
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