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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 500,000
Max Cl/Cd: 110.6 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe234-il-500000.txt
Download as CSV file: xf-goe234-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0367   0.08363   0.08091  -0.1025   0.8796   0.0439
  -9.000  -0.0968   0.06268   0.05985  -0.1149   0.8706   0.0380
  -8.750  -0.1119   0.03447   0.03083  -0.1684   0.8584   0.0368
  -8.500  -0.0383   0.02606   0.02173  -0.1960   0.8542   0.0378
  -8.250  -0.0029   0.02412   0.01969  -0.2004   0.8494   0.0386
  -8.000   0.0328   0.02295   0.01846  -0.2040   0.8448   0.0394
  -7.750   0.0690   0.02188   0.01727  -0.2074   0.8403   0.0404
  -7.500   0.1073   0.02053   0.01575  -0.2115   0.8358   0.0415
  -7.250   0.1441   0.01936   0.01442  -0.2148   0.8311   0.0423
  -7.000   0.1802   0.01843   0.01332  -0.2176   0.8264   0.0431
  -6.750   0.2126   0.01766   0.01241  -0.2189   0.8219   0.0440
  -6.500   0.2421   0.01724   0.01203  -0.2193   0.8171   0.0452
  -6.250   0.2744   0.01679   0.01155  -0.2206   0.8119   0.0463
  -6.000   0.3065   0.01640   0.01109  -0.2216   0.8072   0.0473
  -5.750   0.3384   0.01610   0.01070  -0.2226   0.8025   0.0485
  -5.500   0.3708   0.01574   0.01031  -0.2237   0.7972   0.0497
  -5.250   0.4025   0.01546   0.00998  -0.2245   0.7918   0.0511
  -5.000   0.4339   0.01526   0.00976  -0.2253   0.7869   0.0530
  -4.750   0.4670   0.01494   0.00943  -0.2266   0.7817   0.0549
  -4.500   0.5001   0.01460   0.00905  -0.2280   0.7759   0.0570
  -4.250   0.5330   0.01429   0.00865  -0.2292   0.7704   0.0587
  -4.000   0.5688   0.01377   0.00811  -0.2315   0.7648   0.0627
  -3.750   0.6036   0.01325   0.00754  -0.2334   0.7585   0.0667
  -3.500   0.6414   0.01237   0.00653  -0.2365   0.7528   0.0725
  -3.250   0.6771   0.01163   0.00566  -0.2388   0.7467   0.0797
  -3.000   0.7187   0.00998   0.00423  -0.2435   0.7398   0.2054
  -2.750   0.7480   0.01004   0.00436  -0.2436   0.7334   0.2683
  -2.500   0.7770   0.01017   0.00446  -0.2435   0.7261   0.2814
  -2.250   0.8048   0.01046   0.00477  -0.2430   0.7181   0.2885
  -2.000   0.8334   0.01064   0.00487  -0.2429   0.7095   0.2955
  -1.750   0.8611   0.01087   0.00509  -0.2425   0.7006   0.2996
  -1.500   0.8883   0.01123   0.00549  -0.2419   0.6920   0.3029
  -1.250   0.9157   0.01153   0.00575  -0.2414   0.6834   0.3068
  -1.000   0.9447   0.01163   0.00577  -0.2415   0.6747   0.3111
  -0.750   0.9725   0.01180   0.00587  -0.2413   0.6655   0.3139
  -0.500   0.9996   0.01205   0.00615  -0.2408   0.6549   0.3155
  -0.250   1.0258   0.01242   0.00649  -0.2400   0.6451   0.3172
   0.000   1.0515   0.01285   0.00698  -0.2391   0.6363   0.3192
   0.250   1.0787   0.01308   0.00716  -0.2388   0.6292   0.3213
   0.500   1.1087   0.01297   0.00700  -0.2393   0.6220   0.3243
   0.750   1.1393   0.01285   0.00671  -0.2401   0.6151   0.3281
   1.000   1.1682   0.01279   0.00662  -0.2404   0.6088   0.3297
   1.250   1.1964   0.01283   0.00666  -0.2404   0.6019   0.3307
   1.500   1.2237   0.01298   0.00677  -0.2402   0.5955   0.3318
   1.750   1.2514   0.01309   0.00691  -0.2401   0.5891   0.3332
   2.000   1.2787   0.01323   0.00705  -0.2399   0.5823   0.3346
   2.250   1.3063   0.01333   0.00711  -0.2398   0.5760   0.3359
   2.500   1.3346   0.01333   0.00711  -0.2399   0.5691   0.3375
   2.750   1.3623   0.01338   0.00711  -0.2400   0.5622   0.3393
   3.000   1.3904   0.01339   0.00709  -0.2401   0.5555   0.3414
   3.250   1.4181   0.01345   0.00710  -0.2401   0.5479   0.3438
   3.500   1.4452   0.01354   0.00713  -0.2400   0.5408   0.3455
   3.750   1.4723   0.01356   0.00718  -0.2399   0.5328   0.3469
   4.000   1.4979   0.01372   0.00732  -0.2395   0.5247   0.3480
   4.250   1.5240   0.01383   0.00746  -0.2392   0.5150   0.3492
   4.500   1.5488   0.01402   0.00763  -0.2386   0.5041   0.3505
   4.750   1.5729   0.01424   0.00782  -0.2379   0.4918   0.3520
   5.000   1.5971   0.01444   0.00800  -0.2372   0.4781   0.3536
   5.250   1.6201   0.01470   0.00822  -0.2363   0.4625   0.3554
   5.500   1.6421   0.01500   0.00846  -0.2353   0.4459   0.3573
   5.750   1.6629   0.01536   0.00874  -0.2341   0.4280   0.3593
   6.000   1.6817   0.01582   0.00910  -0.2325   0.4083   0.3609
   6.250   1.6987   0.01633   0.00950  -0.2306   0.3867   0.3626
   6.500   1.7132   0.01691   0.00999  -0.2282   0.3647   0.3642
   6.750   1.7249   0.01759   0.01058  -0.2254   0.3448   0.3655
   7.000   1.7313   0.01829   0.01122  -0.2215   0.3280   0.3667
   7.250   1.7408   0.01902   0.01190  -0.2183   0.3138   0.3681
   7.500   1.7527   0.01978   0.01263  -0.2157   0.3019   0.3696
   7.750   1.7647   0.02058   0.01339  -0.2132   0.2911   0.3713
   8.000   1.7791   0.02128   0.01408  -0.2112   0.2822   0.3730
   8.500   1.8052   0.02287   0.01567  -0.2069   0.2662   0.3766
   8.750   1.8168   0.02380   0.01657  -0.2046   0.2590   0.3779
   9.000   1.8309   0.02457   0.01738  -0.2028   0.2529   0.3796
   9.250   1.8438   0.02544   0.01830  -0.2009   0.2461   0.3813
   9.500   1.8536   0.02656   0.01942  -0.1986   0.2391   0.3829
   9.750   1.8675   0.02742   0.02034  -0.1969   0.2324   0.3849
  10.000   1.8754   0.02874   0.02165  -0.1945   0.2245   0.3868
  10.250   1.8880   0.02975   0.02271  -0.1928   0.2162   0.3887
  10.500   1.8952   0.03121   0.02415  -0.1906   0.2064   0.3904
  10.750   1.9010   0.03283   0.02572  -0.1883   0.1921   0.3919
  11.000   1.9032   0.03479   0.02759  -0.1858   0.1674   0.3933
  11.250   1.8779   0.03920   0.03161  -0.1809   0.1157   0.3936
  11.500   1.8589   0.04327   0.03552  -0.1770   0.0881   0.3942
  11.750   1.8377   0.04783   0.03990  -0.1734   0.0540   0.3948
  12.000   1.8282   0.05142   0.04345  -0.1709   0.0423   0.3959
  12.250   1.8268   0.05426   0.04636  -0.1691   0.0392   0.3971
  12.500   1.8251   0.05723   0.04940  -0.1674   0.0369   0.3984
  12.750   1.8264   0.05994   0.05221  -0.1661   0.0356   0.3998
  13.000   1.8261   0.06288   0.05526  -0.1647   0.0345   0.4014
  13.250   1.8238   0.06614   0.05862  -0.1635   0.0334   0.4031
  13.500   1.8187   0.06980   0.06237  -0.1623   0.0324   0.4046
  13.750   1.8109   0.07393   0.06661  -0.1612   0.0314   0.4060
  14.000   1.8057   0.07781   0.07060  -0.1603   0.0307   0.4074
  14.250   1.8036   0.08128   0.07419  -0.1595   0.0301   0.4087
  14.500   1.7997   0.08505   0.07807  -0.1589   0.0295   0.4097
  14.750   1.7945   0.08908   0.08222  -0.1585   0.0289   0.4111
  15.000   1.7879   0.09338   0.08663  -0.1582   0.0283   0.4124
  15.250   1.7801   0.09788   0.09124  -0.1580   0.0277   0.4135
  15.500   1.7701   0.10275   0.09622  -0.1580   0.0272   0.4146
  15.750   1.7576   0.10805   0.10163  -0.1582   0.0267   0.4156
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