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GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il)
Reynolds number: 500,000
Max Cl/Cd: 100.14 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe308-il-500000-n5.txt
Download as CSV file: xf-goe308-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 308 (MVA H.40) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3257   0.10021   0.09801  -0.0275   1.0000   0.0078
  -9.000  -0.3277   0.09707   0.09491  -0.0275   1.0000   0.0079
  -8.750  -0.3292   0.09242   0.09029  -0.0294   0.9993   0.0083
  -8.500  -0.3133   0.08893   0.08680  -0.0337   0.9966   0.0088
  -8.250  -0.3020   0.08471   0.08259  -0.0381   0.9922   0.0089
  -8.000  -0.2857   0.08176   0.07963  -0.0420   0.9875   0.0093
  -7.750  -0.2766   0.07753   0.07541  -0.0468   0.9788   0.0094
  -7.250  -0.2476   0.06793   0.06577  -0.0581   0.9584   0.0102
  -6.250  -0.1543   0.03361   0.03056  -0.0917   0.9024   0.0159
  -6.000  -0.1239   0.03246   0.02929  -0.0935   0.8874   0.0163
  -5.750  -0.0943   0.03231   0.02905  -0.0945   0.8710   0.0170
  -5.500  -0.0977   0.01890   0.01445  -0.0924   0.8541   0.0204
  -5.250  -0.0738   0.01774   0.01292  -0.0917   0.8401   0.0214
  -5.000  -0.0528   0.01618   0.01102  -0.0908   0.8276   0.0224
  -4.750  -0.0289   0.01559   0.01030  -0.0901   0.8158   0.0232
  -4.500  -0.0046   0.01506   0.00960  -0.0894   0.8038   0.0239
  -4.250   0.0199   0.01463   0.00902  -0.0888   0.7909   0.0249
  -4.000   0.0442   0.01409   0.00830  -0.0880   0.7781   0.0258
  -3.750   0.0686   0.01344   0.00746  -0.0872   0.7652   0.0265
  -3.500   0.0931   0.01285   0.00666  -0.0864   0.7516   0.0271
  -3.250   0.1179   0.01246   0.00611  -0.0857   0.7357   0.0280
  -3.000   0.1423   0.01212   0.00559  -0.0848   0.7168   0.0287
  -2.750   0.1667   0.01177   0.00506  -0.0840   0.6969   0.0291
  -2.500   0.1911   0.01151   0.00463  -0.0831   0.6762   0.0294
  -2.000   0.2394   0.01110   0.00392  -0.0813   0.6349   0.0298
  -1.750   0.2634   0.01087   0.00355  -0.0804   0.6149   0.0300
  -1.500   0.2872   0.01060   0.00315  -0.0795   0.5965   0.0304
  -1.250   0.3110   0.01037   0.00281  -0.0786   0.5781   0.0310
  -1.000   0.3350   0.01020   0.00254  -0.0777   0.5596   0.0319
  -0.750   0.3590   0.01013   0.00236  -0.0768   0.5393   0.0324
  -0.500   0.3831   0.01009   0.00222  -0.0760   0.5208   0.0326
  -0.250   0.4074   0.01007   0.00211  -0.0752   0.5040   0.0331
   0.000   0.4318   0.01006   0.00200  -0.0744   0.4883   0.0340
   0.250   0.4563   0.01008   0.00194  -0.0736   0.4744   0.0350
   0.500   0.4809   0.01009   0.00188  -0.0729   0.4624   0.0366
   0.750   0.5059   0.01010   0.00184  -0.0723   0.4532   0.0387
   1.250   0.5552   0.01009   0.00189  -0.0710   0.4368   0.0755
   1.500   0.5801   0.01017   0.00195  -0.0703   0.4285   0.0912
   1.750   0.6052   0.01025   0.00201  -0.0698   0.4199   0.0990
   2.000   0.6302   0.01033   0.00207  -0.0692   0.4126   0.1047
   2.250   0.6552   0.01038   0.00214  -0.0687   0.4056   0.1108
   2.500   0.6800   0.01047   0.00220  -0.0681   0.3994   0.1155
   2.750   0.7054   0.01051   0.00227  -0.0676   0.3934   0.1200
   3.000   0.7300   0.01058   0.00235  -0.0669   0.3869   0.1283
   3.500   0.7785   0.01059   0.00259  -0.0656   0.3737   0.2228
   3.750   0.7846   0.00954   0.00270  -0.0614   0.3696   0.7466
   4.250   0.8983   0.00968   0.00331  -0.0743   0.3558   0.9813
   4.500   0.9354   0.00984   0.00349  -0.0765   0.3502   0.9890
   4.750   0.9687   0.01000   0.00365  -0.0779   0.3436   0.9933
   5.000   1.0030   0.01018   0.00383  -0.0795   0.3355   0.9968
   5.250   1.0380   0.01039   0.00400  -0.0814   0.3205   0.9995
   5.500   1.0615   0.01060   0.00417  -0.0807   0.3067   1.0000
   5.750   1.0811   0.01083   0.00435  -0.0791   0.2907   1.0000
   6.000   1.0989   0.01118   0.00459  -0.0773   0.2665   1.0000
   6.250   1.1147   0.01164   0.00489  -0.0751   0.2329   1.0000
   6.750   1.1434   0.01282   0.00571  -0.0703   0.1702   1.0000
   7.000   1.1579   0.01340   0.00617  -0.0680   0.1448   1.0000
   7.250   1.1579   0.01491   0.00715  -0.0633   0.0607   1.0000
   7.500   1.1646   0.01597   0.00803  -0.0596   0.0204   1.0000
   7.750   1.1809   0.01640   0.00850  -0.0576   0.0163   1.0000
   8.000   1.1970   0.01683   0.00899  -0.0555   0.0144   1.0000
   8.250   1.2115   0.01735   0.00955  -0.0532   0.0126   1.0000
   8.500   1.2230   0.01795   0.01024  -0.0503   0.0111   1.0000
   8.750   1.2354   0.01841   0.01078  -0.0477   0.0106   1.0000
   9.000   1.2464   0.01896   0.01140  -0.0448   0.0101   1.0000
   9.250   1.2573   0.01955   0.01206  -0.0420   0.0094   1.0000
   9.500   1.2678   0.02020   0.01278  -0.0393   0.0089   1.0000
   9.750   1.2784   0.02087   0.01348  -0.0368   0.0082   1.0000
  10.000   1.2829   0.02193   0.01464  -0.0335   0.0077   1.0000
  10.250   1.2893   0.02291   0.01571  -0.0307   0.0075   1.0000
  10.500   1.2993   0.02373   0.01663  -0.0285   0.0070   1.0000
  10.750   1.3043   0.02490   0.01790  -0.0259   0.0069   1.0000
  11.000   1.3097   0.02612   0.01921  -0.0236   0.0066   1.0000
  11.250   1.3150   0.02741   0.02059  -0.0215   0.0063   1.0000
  11.500   1.3176   0.02901   0.02228  -0.0195   0.0061   1.0000
  11.750   1.3195   0.03078   0.02415  -0.0177   0.0059   1.0000
  12.000   1.3207   0.03272   0.02619  -0.0162   0.0058   1.0000
  12.250   1.3218   0.03482   0.02837  -0.0149   0.0056   1.0000
  12.500   1.3203   0.03728   0.03094  -0.0139   0.0055   1.0000
  12.750   1.3187   0.03994   0.03369  -0.0132   0.0054   1.0000
  13.000   1.3102   0.04348   0.03733  -0.0128   0.0052   1.0000
  13.250   1.3039   0.04698   0.04096  -0.0127   0.0052   1.0000
  13.500   1.3021   0.05009   0.04421  -0.0127   0.0050   1.0000
  13.750   1.2952   0.05386   0.04809  -0.0129   0.0050   1.0000
  14.000   1.2911   0.05741   0.05176  -0.0132   0.0049   1.0000
  14.250   1.2902   0.06068   0.05513  -0.0138   0.0048   1.0000
  14.500   1.2884   0.06411   0.05867  -0.0144   0.0045   1.0000
  14.750   1.2834   0.06796   0.06263  -0.0150   0.0045   1.0000
  15.000   1.2773   0.07198   0.06675  -0.0156   0.0045   1.0000
  15.250   1.2730   0.07587   0.07075  -0.0164   0.0043   1.0000
  15.500   1.2687   0.07972   0.07470  -0.0172   0.0043   1.0000
  15.750   1.2645   0.08369   0.07877  -0.0181   0.0041   1.0000
  16.000   1.2605   0.08762   0.08280  -0.0190   0.0041   1.0000
  16.250   1.2566   0.09161   0.08689  -0.0200   0.0040   1.0000
  16.500   1.2527   0.09564   0.09102  -0.0211   0.0040   1.0000
  16.750   1.2479   0.09969   0.09518  -0.0220   0.0040   1.0000
  17.000   1.2445   0.10389   0.09947  -0.0235   0.0039   1.0000
  17.250   1.2397   0.10821   0.10390  -0.0248   0.0039   1.0000
  17.500   1.2361   0.11263   0.10839  -0.0267   0.0037   1.0000
  17.750   1.2312   0.11702   0.11289  -0.0282   0.0037   1.0000
  18.000   1.2266   0.12160   0.11759  -0.0301   0.0037   1.0000
  18.250   1.2219   0.12626   0.12234  -0.0321   0.0036   1.0000
  18.500   1.2151   0.13121   0.12744  -0.0340   0.0037   1.0000
  18.750   1.2114   0.13591   0.13220  -0.0364   0.0036   1.0000
  19.000   1.2047   0.14114   0.13756  -0.0388   0.0036   1.0000
  19.250   1.1984   0.14644   0.14297  -0.0416   0.0035   1.0000
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