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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 500,000
Max Cl/Cd: 93.71 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe134-il-500000-n5.txt
Download as CSV file: xf-goe134-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 134 (MVA H.12) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3814   0.08934   0.08714  -0.0260   1.0000   0.0089
  -8.000  -0.3819   0.08654   0.08437  -0.0266   1.0000   0.0092
  -7.750  -0.3898   0.08415   0.08202  -0.0258   1.0000   0.0093
  -7.500  -0.3817   0.07990   0.07778  -0.0305   0.9968   0.0098
  -7.250  -0.3641   0.07384   0.07170  -0.0391   0.9918   0.0101
  -7.000  -0.3437   0.06667   0.06447  -0.0489   0.9866   0.0104
  -6.750  -0.3233   0.05648   0.05412  -0.0602   0.9793   0.0110
  -6.500  -0.2975   0.05314   0.05070  -0.0643   0.9749   0.0113
  -6.250  -0.2738   0.05020   0.04768  -0.0671   0.9677   0.0116
  -6.000  -0.2480   0.04646   0.04380  -0.0705   0.9611   0.0124
  -5.750  -0.2227   0.03590   0.03271  -0.0754   0.9526   0.0141
  -5.500  -0.1978   0.03441   0.03112  -0.0761   0.9439   0.0144
  -5.250  -0.1725   0.03276   0.02934  -0.0768   0.9342   0.0148
  -5.000  -0.1476   0.03043   0.02680  -0.0771   0.9221   0.0159
  -4.750  -0.1210   0.02413   0.01982  -0.0772   0.9095   0.0179
  -4.500  -0.0959   0.02340   0.01897  -0.0771   0.8923   0.0182
  -4.250  -0.0707   0.02257   0.01798  -0.0769   0.8699   0.0189
  -4.000  -0.0450   0.02101   0.01608  -0.0764   0.8395   0.0201
  -3.750  -0.0181   0.01867   0.01309  -0.0756   0.8022   0.0214
  -3.500   0.0078   0.01748   0.01149  -0.0753   0.7673   0.0224
  -3.000   0.0616   0.01634   0.01000  -0.0753   0.7233   0.0236
  -2.750   0.0895   0.01555   0.00897  -0.0753   0.7086   0.0240
  -2.250   0.1460   0.01425   0.00730  -0.0753   0.6827   0.0252
  -2.000   0.1744   0.01377   0.00666  -0.0753   0.6701   0.0260
  -1.750   0.2027   0.01326   0.00601  -0.0753   0.6578   0.0263
  -1.500   0.2310   0.01287   0.00550  -0.0754   0.6447   0.0266
  -1.250   0.2593   0.01257   0.00509  -0.0754   0.6313   0.0269
  -1.000   0.2875   0.01233   0.00474  -0.0755   0.6168   0.0271
  -0.750   0.3155   0.01195   0.00429  -0.0755   0.6019   0.0274
  -0.500   0.3433   0.01141   0.00371  -0.0756   0.5862   0.0280
  -0.250   0.3712   0.01114   0.00339  -0.0757   0.5707   0.0287
   0.000   0.3993   0.01096   0.00315  -0.0758   0.5555   0.0289
   0.250   0.4275   0.01081   0.00293  -0.0759   0.5404   0.0291
   0.500   0.4556   0.01070   0.00276  -0.0760   0.5257   0.0294
   0.750   0.4838   0.01061   0.00263  -0.0762   0.5121   0.0299
   1.000   0.5121   0.01056   0.00252  -0.0763   0.4990   0.0304
   1.250   0.5404   0.01053   0.00245  -0.0765   0.4856   0.0311
   1.500   0.5685   0.01053   0.00240  -0.0766   0.4715   0.0318
   1.750   0.5966   0.01056   0.00237  -0.0767   0.4574   0.0325
   2.000   0.6247   0.01061   0.00237  -0.0768   0.4444   0.0334
   2.250   0.6527   0.01068   0.00238  -0.0769   0.4319   0.0347
   2.500   0.6807   0.01075   0.00240  -0.0770   0.4195   0.0357
   3.000   0.7364   0.01094   0.00251  -0.0772   0.3943   0.0398
   3.250   0.7640   0.00991   0.00275  -0.0781   0.3822   0.6280
   3.750   0.8120   0.00934   0.00293  -0.0763   0.3616   1.0000
   4.000   0.8397   0.00950   0.00306  -0.0763   0.3518   1.0000
   4.250   0.8671   0.00970   0.00320  -0.0764   0.3413   1.0000
   4.500   0.8943   0.00992   0.00336  -0.0764   0.3306   1.0000
   4.750   0.9216   0.01012   0.00354  -0.0765   0.3198   1.0000
   5.000   0.9488   0.01033   0.00371  -0.0765   0.3094   1.0000
   5.250   0.9757   0.01057   0.00391  -0.0765   0.2984   1.0000
   5.500   1.0024   0.01082   0.00412  -0.0765   0.2869   1.0000
   5.750   1.0292   0.01105   0.00433  -0.0765   0.2749   1.0000
   6.000   1.0558   0.01130   0.00455  -0.0764   0.2640   1.0000
   6.250   1.0823   0.01155   0.00479  -0.0764   0.2545   1.0000
   6.500   1.1084   0.01185   0.00505  -0.0763   0.2422   1.0000
   6.750   1.1341   0.01216   0.00532  -0.0761   0.2272   1.0000
   7.000   1.1597   0.01250   0.00561  -0.0760   0.2118   1.0000
   7.250   1.1848   0.01287   0.00595  -0.0758   0.1937   1.0000
   7.500   1.2087   0.01338   0.00634  -0.0754   0.1677   1.0000
   7.750   1.2295   0.01423   0.00694  -0.0746   0.1255   1.0000
   8.000   1.2507   0.01500   0.00757  -0.0739   0.0994   1.0000
   8.250   1.2723   0.01569   0.00816  -0.0732   0.0789   1.0000
   8.500   1.2931   0.01643   0.00879  -0.0724   0.0596   1.0000
   8.750   1.3130   0.01723   0.00949  -0.0714   0.0417   1.0000
   9.000   1.3286   0.01843   0.01052  -0.0698   0.0165   1.0000
   9.250   1.3493   0.01904   0.01121  -0.0689   0.0141   1.0000
   9.500   1.3686   0.01976   0.01200  -0.0678   0.0124   1.0000
   9.750   1.3874   0.02047   0.01279  -0.0666   0.0111   1.0000
  10.000   1.4063   0.02111   0.01352  -0.0654   0.0102   1.0000
  10.250   1.4238   0.02182   0.01433  -0.0641   0.0095   1.0000
  10.500   1.4391   0.02263   0.01522  -0.0624   0.0089   1.0000
  10.750   1.4511   0.02361   0.01629  -0.0602   0.0084   1.0000
  11.000   1.4601   0.02462   0.01740  -0.0576   0.0080   1.0000
  11.250   1.4688   0.02554   0.01843  -0.0549   0.0077   1.0000
  11.500   1.4770   0.02658   0.01956  -0.0524   0.0074   1.0000
  11.750   1.4841   0.02775   0.02085  -0.0500   0.0071   1.0000
  12.000   1.4908   0.02904   0.02223  -0.0478   0.0067   1.0000
  12.250   1.4965   0.03047   0.02376  -0.0458   0.0064   1.0000
  12.500   1.5008   0.03213   0.02551  -0.0439   0.0062   1.0000
  12.750   1.5023   0.03414   0.02763  -0.0422   0.0060   1.0000
  13.000   1.5006   0.03665   0.03026  -0.0408   0.0058   1.0000
  13.250   1.4944   0.03988   0.03363  -0.0398   0.0057   1.0000
  13.500   1.4941   0.04274   0.03662  -0.0394   0.0056   1.0000
  13.750   1.4924   0.04594   0.03996  -0.0394   0.0055   1.0000
  14.000   1.4886   0.04951   0.04368  -0.0396   0.0054   1.0000
  14.250   1.4830   0.05346   0.04776  -0.0401   0.0053   1.0000
  14.500   1.4764   0.05765   0.05208  -0.0408   0.0053   1.0000
  14.750   1.4681   0.06216   0.05674  -0.0417   0.0052   1.0000
  15.000   1.4588   0.06694   0.06165  -0.0429   0.0051   1.0000
  15.250   1.4485   0.07199   0.06683  -0.0442   0.0050   1.0000
  15.500   1.4377   0.07719   0.07216  -0.0456   0.0050   1.0000
  15.750   1.4266   0.08257   0.07767  -0.0473   0.0049   1.0000
  16.000   1.4153   0.08810   0.08332  -0.0490   0.0049   1.0000
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