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GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 612 AIRFOIL (goe612-il)
Reynolds number: 100,000
Max Cl/Cd: 51.32 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe612-il-100000.txt
Download as CSV file: xf-goe612-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 612 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2144   0.10292   0.09827  -0.0536   0.9661   0.1529
  -8.000  -0.2528   0.10137   0.09679  -0.0638   0.9530   0.1604
  -7.750  -0.2215   0.09660   0.09202  -0.0625   0.9487   0.1625
  -7.500  -0.1853   0.09365   0.08902  -0.0625   0.9447   0.1672
  -7.250  -0.1919   0.09145   0.08685  -0.0667   0.9355   0.1750
  -7.000  -0.2110   0.08810   0.08354  -0.0706   0.9248   0.1786
  -6.750  -0.1662   0.08485   0.08025  -0.0708   0.9238   0.1823
  -6.500  -0.1758   0.08370   0.07914  -0.0680   0.9126   0.1855
  -6.000  -0.3093   0.04787   0.04123  -0.0902   0.8847   0.1029
  -5.750  -0.2964   0.04525   0.03832  -0.0894   0.8788   0.1025
  -5.500  -0.2717   0.04221   0.03488  -0.0905   0.8749   0.1036
  -5.250  -0.2492   0.04083   0.03350  -0.0905   0.8702   0.1056
  -5.000  -0.2406   0.03980   0.03229  -0.0881   0.8631   0.1067
  -4.750  -0.2143   0.03824   0.03043  -0.0884   0.8591   0.1084
  -4.500  -0.1790   0.03660   0.02840  -0.0899   0.8562   0.1109
  -4.250  -0.1749   0.03616   0.02773  -0.0864   0.8486   0.1127
  -4.000  -0.1513   0.03531   0.02652  -0.0859   0.8438   0.1164
  -3.750  -0.1184   0.03443   0.02569  -0.0870   0.8405   0.1220
  -3.500  -0.0871   0.03377   0.02479  -0.0874   0.8368   0.1283
  -3.250  -0.0824   0.03363   0.02462  -0.0841   0.8291   0.1320
  -3.000  -0.0535   0.03323   0.02420  -0.0843   0.8250   0.1424
  -2.750  -0.0153   0.03249   0.02351  -0.0858   0.8220   0.1578
  -2.500  -0.0108   0.03269   0.02380  -0.0826   0.8145   0.1683
  -2.250   0.0129   0.03252   0.02366  -0.0820   0.8092   0.1915
  -2.000   0.0491   0.03212   0.02342  -0.0831   0.8055   0.2258
  -1.750   0.0610   0.03243   0.02381  -0.0808   0.7979   0.2486
  -1.500   0.0921   0.03219   0.02369  -0.0810   0.7906   0.2843
  -1.250   0.1493   0.03123   0.02290  -0.0844   0.7864   0.3403
  -1.000   0.1534   0.03163   0.02341  -0.0806   0.7739   0.3660
  -0.750   0.2040   0.03072   0.02262  -0.0830   0.7699   0.4195
  -0.500   0.2050   0.03147   0.02343  -0.0792   0.7590   0.4409
  -0.250   0.2450   0.03090   0.02293  -0.0803   0.7545   0.4805
   0.000   0.2957   0.02987   0.02198  -0.0829   0.7519   0.5253
   0.250   0.2929   0.03079   0.02301  -0.0786   0.7396   0.5463
   0.500   0.3432   0.02968   0.02209  -0.0811   0.7362   0.6003
   0.750   0.4033   0.02782   0.02091  -0.0846   0.7346   0.7302
   1.000   0.4899   0.02748   0.02076  -0.0959   0.7267   1.0000
   1.250   0.5327   0.02696   0.02003  -0.0977   0.7211   1.0000
   1.500   0.5891   0.02587   0.01875  -0.1011   0.7183   1.0000
   1.750   0.6438   0.02485   0.01755  -0.1043   0.7154   1.0000
   2.000   0.6469   0.02556   0.01821  -0.1002   0.7023   1.0000
   2.250   0.7037   0.02437   0.01688  -0.1036   0.6988   1.0000
   2.500   0.7111   0.02491   0.01739  -0.1001   0.6860   1.0000
   2.750   0.7655   0.02379   0.01614  -0.1031   0.6814   1.0000
   3.000   0.7789   0.02407   0.01638  -0.1003   0.6687   1.0000
   3.250   0.8332   0.02295   0.01513  -0.1034   0.6629   1.0000
   3.500   0.8475   0.02312   0.01528  -0.1007   0.6492   1.0000
   3.750   0.8760   0.02285   0.01495  -0.1000   0.6375   1.0000
   4.000   0.9195   0.02208   0.01404  -0.1015   0.6275   1.0000
   4.250   0.9392   0.02203   0.01395  -0.0995   0.6125   1.0000
   4.500   0.9626   0.02188   0.01375  -0.0981   0.5973   1.0000
   4.750   0.9874   0.02171   0.01350  -0.0969   0.5818   1.0000
   5.000   1.0120   0.02157   0.01327  -0.0957   0.5657   1.0000
   5.250   1.0354   0.02151   0.01311  -0.0944   0.5492   1.0000
   5.500   1.0579   0.02154   0.01305  -0.0930   0.5327   1.0000
   5.750   1.0799   0.02165   0.01304  -0.0916   0.5167   1.0000
   6.000   1.1020   0.02183   0.01309  -0.0903   0.5013   1.0000
   6.250   1.1249   0.02205   0.01318  -0.0891   0.4867   1.0000
   6.500   1.1469   0.02235   0.01335  -0.0879   0.4726   1.0000
   6.750   1.1632   0.02282   0.01376  -0.0859   0.4587   1.0000
   7.000   1.1814   0.02331   0.01418  -0.0843   0.4458   1.0000
   7.250   1.2035   0.02378   0.01454  -0.0832   0.4340   1.0000
   7.500   1.2267   0.02427   0.01490  -0.0825   0.4225   1.0000
   7.750   1.2416   0.02493   0.01558  -0.0804   0.4115   1.0000
   8.000   1.2659   0.02552   0.01606  -0.0799   0.4014   1.0000
   8.250   1.2837   0.02617   0.01669  -0.0784   0.3912   1.0000
   8.500   1.3030   0.02690   0.01741  -0.0772   0.3819   1.0000
   8.750   1.3266   0.02757   0.01800  -0.0767   0.3725   1.0000
   9.000   1.3408   0.02841   0.01889  -0.0747   0.3636   1.0000
   9.250   1.3681   0.02910   0.01945  -0.0748   0.3543   1.0000
   9.500   1.3763   0.03002   0.02049  -0.0720   0.3460   1.0000
   9.750   1.4050   0.03076   0.02110  -0.0723   0.3369   1.0000
  10.000   1.4096   0.03175   0.02225  -0.0690   0.3293   1.0000
  10.250   1.4339   0.03256   0.02299  -0.0688   0.3209   1.0000
  10.500   1.4430   0.03364   0.02417  -0.0662   0.3137   1.0000
  10.750   1.4545   0.03456   0.02514  -0.0640   0.3062   1.0000
  11.000   1.4779   0.03560   0.02614  -0.0638   0.2987   1.0000
  11.250   1.4740   0.03672   0.02745  -0.0594   0.2923   1.0000
  11.500   1.5182   0.03755   0.02806  -0.0623   0.2841   1.0000
  11.750   1.5003   0.03891   0.02971  -0.0561   0.2792   1.0000
  12.000   1.5037   0.04011   0.03104  -0.0532   0.2735   1.0000
  12.250   1.5464   0.04098   0.03173  -0.0556   0.2669   1.0000
  12.500   1.5276   0.04273   0.03379  -0.0501   0.2629   1.0000
  12.750   1.5241   0.04435   0.03558  -0.0468   0.2584   1.0000
  13.000   1.5479   0.04520   0.03641  -0.0466   0.2534   1.0000
  13.250   1.5596   0.04678   0.03806  -0.0453   0.2491   1.0000
  13.500   1.5385   0.04921   0.04078  -0.0408   0.2458   1.0000
  13.750   1.5288   0.05144   0.04320  -0.0379   0.2421   1.0000
  14.000   1.5403   0.05283   0.04465  -0.0367   0.2385   1.0000
  14.250   1.5819   0.05354   0.04527  -0.0382   0.2345   1.0000
  14.500   1.5385   0.05763   0.04972  -0.0332   0.2328   1.0000
  14.750   1.4856   0.06327   0.05571  -0.0293   0.2309   1.0000
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