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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 100,000
Max Cl/Cd: 55.98 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe693-il-100000.txt
Download as CSV file: xf-goe693-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3583   0.10464   0.09947  -0.0388   1.0000   0.1303
  -9.000  -0.3939   0.10351   0.09852  -0.0418   1.0000   0.1326
  -8.750  -0.4304   0.10236   0.09756  -0.0417   1.0000   0.1330
  -8.500  -0.3740   0.09599   0.09104  -0.0381   1.0000   0.1369
  -8.250  -0.3730   0.09372   0.08882  -0.0362   1.0000   0.1397
  -8.000  -0.3839   0.09183   0.08703  -0.0344   1.0000   0.1426
  -7.750  -0.4089   0.09058   0.08591  -0.0316   1.0000   0.1450
  -7.500  -0.4455   0.08973   0.08522  -0.0288   1.0000   0.1466
  -7.250  -0.5051   0.08833   0.08388  -0.0325   1.0000   0.1486
  -7.000  -0.5093   0.08459   0.08020  -0.0301   1.0000   0.1497
  -6.750  -0.5026   0.08234   0.07803  -0.0254   1.0000   0.1511
  -6.500  -0.5022   0.08049   0.07622  -0.0222   1.0000   0.1532
  -6.250  -0.4964   0.07790   0.07362  -0.0226   0.9983   0.1581
  -6.000  -0.4737   0.07192   0.06750  -0.0319   0.9911   0.1684
  -5.750  -0.4476   0.06678   0.06210  -0.0409   0.9838   0.1823
  -5.500  -0.4227   0.04850   0.04265  -0.0536   0.9772   0.1149
  -5.250  -0.3918   0.04322   0.03689  -0.0574   0.9721   0.1119
  -5.000  -0.3606   0.03878   0.03183  -0.0603   0.9669   0.1113
  -4.750  -0.3293   0.03538   0.02786  -0.0623   0.9610   0.1117
  -4.500  -0.2912   0.03285   0.02470  -0.0650   0.9570   0.1154
  -4.250  -0.2605   0.03100   0.02244  -0.0663   0.9512   0.1202
  -4.000  -0.2270   0.02986   0.02121  -0.0679   0.9453   0.1256
  -3.750  -0.1859   0.02851   0.01939  -0.0706   0.9415   0.1345
  -3.500  -0.1590   0.02786   0.01878  -0.0710   0.9347   0.1434
  -3.250  -0.1240   0.02695   0.01772  -0.0727   0.9293   0.1548
  -3.000  -0.0827   0.02622   0.01693  -0.0755   0.9256   0.1708
  -2.750  -0.0588   0.02586   0.01651  -0.0751   0.9180   0.1843
  -2.500  -0.0229   0.02538   0.01604  -0.0770   0.9130   0.2013
  -2.250   0.0194   0.02486   0.01557  -0.0799   0.9096   0.2203
  -2.000   0.0390   0.02475   0.01547  -0.0788   0.9010   0.2343
  -1.750   0.0769   0.02432   0.01514  -0.0809   0.8965   0.2550
  -1.500   0.1104   0.02402   0.01490  -0.0821   0.8912   0.2786
  -1.250   0.1364   0.02372   0.01484  -0.0821   0.8841   0.3080
  -1.000   0.1767   0.02273   0.01447  -0.0845   0.8803   0.4023
  -0.750   0.2522   0.02079   0.01415  -0.0915   0.8794   1.0000
  -0.500   0.2764   0.02091   0.01407  -0.0907   0.8683   1.0000
  -0.250   0.3309   0.02031   0.01325  -0.0949   0.8632   1.0000
   0.000   0.3528   0.02043   0.01324  -0.0936   0.8517   1.0000
   0.250   0.3967   0.02007   0.01273  -0.0960   0.8474   1.0000
   0.500   0.4127   0.02050   0.01308  -0.0940   0.8367   1.0000
   0.750   0.4524   0.02022   0.01270  -0.0956   0.8323   1.0000
   1.000   0.4702   0.02064   0.01306  -0.0940   0.8219   1.0000
   1.250   0.5081   0.02035   0.01270  -0.0952   0.8169   1.0000
   1.500   0.5278   0.02071   0.01302  -0.0937   0.8065   1.0000
   1.750   0.5654   0.02034   0.01259  -0.0947   0.8010   1.0000
   2.000   0.5865   0.02061   0.01283  -0.0933   0.7900   1.0000
   2.250   0.6248   0.02012   0.01229  -0.0942   0.7843   1.0000
   2.500   0.6457   0.02036   0.01253  -0.0927   0.7723   1.0000
   2.750   0.6734   0.02029   0.01243  -0.0920   0.7622   1.0000
   3.000   0.7072   0.01986   0.01196  -0.0921   0.7534   1.0000
   3.250   0.7309   0.01992   0.01203  -0.0908   0.7407   1.0000
   3.500   0.7576   0.01986   0.01196  -0.0900   0.7291   1.0000
   3.750   0.7914   0.01948   0.01153  -0.0900   0.7202   1.0000
   4.000   0.8148   0.01959   0.01167  -0.0888   0.7066   1.0000
   4.250   0.8396   0.01964   0.01173  -0.0877   0.6931   1.0000
   4.500   0.8656   0.01960   0.01171  -0.0868   0.6793   1.0000
   4.750   0.8920   0.01956   0.01168  -0.0859   0.6653   1.0000
   5.000   0.9185   0.01952   0.01164  -0.0851   0.6509   1.0000
   5.250   0.9443   0.01947   0.01159  -0.0841   0.6350   1.0000
   5.500   0.9693   0.01943   0.01156  -0.0831   0.6179   1.0000
   5.750   0.9941   0.01942   0.01155  -0.0820   0.6004   1.0000
   6.000   1.0188   0.01944   0.01156  -0.0809   0.5826   1.0000
   6.250   1.0435   0.01948   0.01159  -0.0799   0.5646   1.0000
   6.500   1.0681   0.01955   0.01163  -0.0789   0.5466   1.0000
   6.750   1.0893   0.01979   0.01189  -0.0774   0.5264   1.0000
   7.000   1.1113   0.02002   0.01212  -0.0761   0.5062   1.0000
   7.250   1.1336   0.02025   0.01230  -0.0748   0.4859   1.0000
   7.500   1.1534   0.02063   0.01265  -0.0732   0.4635   1.0000
   7.750   1.1732   0.02106   0.01302  -0.0716   0.4412   1.0000
   8.000   1.1919   0.02162   0.01351  -0.0699   0.4180   1.0000
   8.250   1.2099   0.02228   0.01410  -0.0682   0.3945   1.0000
   8.500   1.2275   0.02308   0.01482  -0.0664   0.3713   1.0000
   8.750   1.2446   0.02395   0.01562  -0.0647   0.3488   1.0000
   9.000   1.2632   0.02488   0.01640  -0.0633   0.3287   1.0000
   9.250   1.2759   0.02571   0.01729  -0.0609   0.3085   1.0000
   9.500   1.2864   0.02644   0.01805  -0.0583   0.2889   1.0000
   9.750   1.2942   0.02712   0.01873  -0.0552   0.2703   1.0000
  10.000   1.3000   0.02784   0.01944  -0.0520   0.2529   1.0000
  10.250   1.3034   0.02864   0.02023  -0.0484   0.2370   1.0000
  10.500   1.3071   0.02961   0.02122  -0.0452   0.2216   1.0000
  10.750   1.3111   0.03075   0.02237  -0.0422   0.2065   1.0000
  11.000   1.3146   0.03210   0.02368  -0.0395   0.1918   1.0000
  11.250   1.3172   0.03367   0.02522  -0.0368   0.1767   1.0000
  11.500   1.3177   0.03545   0.02701  -0.0342   0.1609   1.0000
  11.750   1.3144   0.03749   0.02911  -0.0315   0.1436   1.0000
  12.000   1.3072   0.03983   0.03151  -0.0290   0.1247   1.0000
  12.250   1.2988   0.04253   0.03414  -0.0269   0.1074   1.0000
  12.500   1.2928   0.04539   0.03693  -0.0251   0.0939   1.0000
  12.750   1.2895   0.04818   0.03954  -0.0233   0.0847   1.0000
  13.000   1.2926   0.05065   0.04211  -0.0217   0.0773   1.0000
  13.250   1.2997   0.05293   0.04428  -0.0200   0.0718   1.0000
  13.500   1.3044   0.05531   0.04685  -0.0188   0.0673   1.0000
  13.750   1.3133   0.05738   0.04882  -0.0177   0.0633   1.0000
  14.000   1.3231   0.05974   0.05133  -0.0164   0.0604   1.0000
  14.250   1.3290   0.06234   0.05418  -0.0153   0.0583   1.0000
  14.500   1.3348   0.06495   0.05695  -0.0144   0.0563   1.0000
  14.750   1.3429   0.06735   0.05939  -0.0136   0.0544   1.0000
  15.000   1.3551   0.07008   0.06213  -0.0127   0.0525   1.0000
  15.250   1.3459   0.07393   0.06631  -0.0121   0.0517   1.0000
  15.500   1.3352   0.07811   0.07080  -0.0120   0.0510   1.0000
  15.750   1.3227   0.08267   0.07564  -0.0121   0.0505   1.0000
  16.000   1.3077   0.08771   0.08097  -0.0128   0.0501   1.0000
  16.250   1.2895   0.09339   0.08693  -0.0141   0.0500   1.0000
  16.500   1.2680   0.09982   0.09363  -0.0162   0.0501   1.0000
  16.750   1.2431   0.10718   0.10126  -0.0194   0.0503   1.0000
  17.000   1.2152   0.11564   0.10998  -0.0238   0.0507   1.0000
  17.250   1.1846   0.12537   0.11994  -0.0295   0.0512   1.0000
  17.500   1.1521   0.13651   0.13127  -0.0365   0.0519   1.0000
  17.750   1.1213   0.14837   0.14326  -0.0440   0.0526   1.0000
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