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GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il)
Reynolds number: 100,000
Max Cl/Cd: 56.74 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe336-il-100000.txt
Download as CSV file: xf-goe336-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 336 (MVA H.44) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3008   0.10587   0.10118  -0.0288   1.0000   0.0699
  -8.250  -0.3132   0.10580   0.10125  -0.0312   1.0000   0.0705
  -8.000  -0.3228   0.10559   0.10113  -0.0346   1.0000   0.0708
  -7.750  -0.3105   0.09836   0.09396  -0.0307   1.0000   0.0721
  -7.500  -0.2980   0.09401   0.08964  -0.0279   1.0000   0.0742
  -7.250  -0.2991   0.09170   0.08740  -0.0267   1.0000   0.0757
  -7.000  -0.3032   0.08975   0.08555  -0.0256   1.0000   0.0772
  -6.750  -0.3129   0.08837   0.08429  -0.0237   1.0000   0.0785
  -6.500  -0.3326   0.08801   0.08406  -0.0200   1.0000   0.0791
  -6.250  -0.3300   0.08617   0.08226  -0.0227   0.9957   0.0815
  -6.000  -0.2776   0.08172   0.07755  -0.0421   0.9826   0.0853
  -5.750  -0.2574   0.07589   0.07181  -0.0411   0.9753   0.0877
  -5.500  -0.2225   0.07161   0.06746  -0.0466   0.9664   0.0934
  -5.250  -0.1670   0.06764   0.06314  -0.0615   0.9557   0.1000
  -5.000  -0.1430   0.06266   0.05821  -0.0625   0.9455   0.1024
  -4.750  -0.1069   0.05887   0.05433  -0.0671   0.9358   0.1081
  -4.500  -0.0630   0.05501   0.05021  -0.0746   0.9263   0.1162
  -4.250  -0.0353   0.05180   0.04695  -0.0762   0.9135   0.1221
  -4.000   0.0009   0.04905   0.04388  -0.0806   0.8999   0.1306
  -3.750   0.0256   0.04602   0.04083  -0.0811   0.8866   0.1356
  -3.500   0.0564   0.04378   0.03829  -0.0831   0.8725   0.1461
  -3.250   0.0824   0.04188   0.03622  -0.0834   0.8584   0.1570
  -3.000   0.1043   0.03930   0.03356  -0.0830   0.8445   0.1661
  -2.750   0.1284   0.03743   0.03151  -0.0829   0.8309   0.1804
  -2.500   0.1524   0.03567   0.02956  -0.0825   0.8180   0.1954
  -2.250   0.1754   0.03407   0.02779  -0.0819   0.8047   0.2128
  -2.000   0.1974   0.03266   0.02620  -0.0811   0.7911   0.2386
  -1.500   0.2727   0.02814   0.02014  -0.0815   0.7680   0.1299
  -1.250   0.3015   0.02605   0.01761  -0.0807   0.7584   0.1159
  -1.000   0.3283   0.02481   0.01608  -0.0800   0.7468   0.1102
  -0.750   0.3557   0.02367   0.01465  -0.0794   0.7369   0.1076
  -0.500   0.3840   0.02272   0.01338  -0.0788   0.7282   0.1074
  -0.250   0.4110   0.02207   0.01252  -0.0783   0.7180   0.1095
   0.000   0.4391   0.02146   0.01167  -0.0778   0.7104   0.1156
   0.250   0.4654   0.02111   0.01131  -0.0775   0.7010   0.1260
   0.500   0.4933   0.02055   0.01072  -0.0772   0.6944   0.1404
   0.750   0.5209   0.01998   0.01031  -0.0770   0.6864   0.1778
   1.000   0.5498   0.01975   0.01014  -0.0771   0.6810   0.2284
   1.250   0.5736   0.01976   0.01039  -0.0767   0.6731   0.2827
   1.500   0.6578   0.01812   0.01002  -0.0880   0.6666   1.0000
   1.750   0.6814   0.01861   0.01040  -0.0874   0.6598   1.0000
   2.000   0.7059   0.01902   0.01070  -0.0869   0.6542   1.0000
   2.250   0.7317   0.01938   0.01091  -0.0864   0.6502   1.0000
   2.500   0.7537   0.02001   0.01156  -0.0858   0.6436   1.0000
   2.750   0.7782   0.02037   0.01185  -0.0851   0.6379   1.0000
   3.000   0.8024   0.02076   0.01218  -0.0844   0.6323   1.0000
   3.250   0.8247   0.02126   0.01270  -0.0836   0.6253   1.0000
   3.500   0.8508   0.02144   0.01278  -0.0829   0.6200   1.0000
   3.750   0.8713   0.02204   0.01345  -0.0820   0.6124   1.0000
   4.000   0.8966   0.02225   0.01361  -0.0813   0.6065   1.0000
   4.250   0.9185   0.02271   0.01413  -0.0803   0.5992   1.0000
   4.500   0.9429   0.02293   0.01434  -0.0794   0.5923   1.0000
   4.750   0.9664   0.02329   0.01472  -0.0786   0.5861   1.0000
   5.000   0.9892   0.02358   0.01504  -0.0776   0.5781   1.0000
   5.250   1.0129   0.02367   0.01516  -0.0765   0.5692   1.0000
   5.500   1.0406   0.02332   0.01472  -0.0756   0.5596   1.0000
   5.750   1.0618   0.02344   0.01491  -0.0742   0.5481   1.0000
   6.000   1.0854   0.02344   0.01495  -0.0731   0.5377   1.0000
   6.250   1.1131   0.02325   0.01470  -0.0724   0.5290   1.0000
   6.500   1.1326   0.02364   0.01526  -0.0710   0.5189   1.0000
   6.750   1.1571   0.02368   0.01533  -0.0701   0.5094   1.0000
   7.000   1.1831   0.02351   0.01515  -0.0692   0.4985   1.0000
   7.250   1.2038   0.02359   0.01535  -0.0677   0.4856   1.0000
   7.500   1.2251   0.02362   0.01547  -0.0663   0.4724   1.0000
   7.750   1.2466   0.02349   0.01540  -0.0648   0.4574   1.0000
   8.000   1.2676   0.02318   0.01513  -0.0631   0.4393   1.0000
   8.250   1.2847   0.02303   0.01504  -0.0609   0.4185   1.0000
   8.500   1.3004   0.02303   0.01514  -0.0586   0.3961   1.0000
   8.750   1.3152   0.02318   0.01538  -0.0563   0.3717   1.0000
   9.000   1.3285   0.02349   0.01577  -0.0539   0.3437   1.0000
   9.250   1.3391   0.02400   0.01622  -0.0512   0.3099   1.0000
   9.500   1.3444   0.02488   0.01684  -0.0479   0.2765   1.0000
   9.750   1.3470   0.02609   0.01785  -0.0445   0.2506   1.0000
  10.000   1.3483   0.02739   0.01902  -0.0410   0.2327   1.0000
  10.250   1.3493   0.02866   0.02027  -0.0375   0.2185   1.0000
  10.500   1.3517   0.02998   0.02162  -0.0346   0.2058   1.0000
  10.750   1.3549   0.03136   0.02310  -0.0320   0.1941   1.0000
  11.000   1.3575   0.03287   0.02468  -0.0297   0.1831   1.0000
  11.250   1.3590   0.03458   0.02643  -0.0277   0.1725   1.0000
  11.500   1.3586   0.03656   0.02846  -0.0260   0.1600   1.0000
  11.750   1.3588   0.03870   0.03066  -0.0247   0.1481   1.0000
  12.000   1.3591   0.04098   0.03302  -0.0237   0.1380   1.0000
  12.250   1.3580   0.04349   0.03559  -0.0228   0.1294   1.0000
  12.500   1.3555   0.04627   0.03842  -0.0221   0.1211   1.0000
  12.750   1.3538   0.04908   0.04136  -0.0215   0.1116   1.0000
  13.000   1.3487   0.05236   0.04470  -0.0212   0.1000   1.0000
  13.250   1.3435   0.05576   0.04818  -0.0210   0.0884   1.0000
  13.500   1.3360   0.05952   0.05196  -0.0209   0.0773   1.0000
  13.750   1.3248   0.06381   0.05619  -0.0211   0.0695   1.0000
  14.000   1.3141   0.06810   0.06050  -0.0213   0.0631   1.0000
  14.250   1.3006   0.07285   0.06517  -0.0217   0.0587   1.0000
  14.500   1.2933   0.07688   0.06935  -0.0218   0.0538   1.0000
  14.750   1.2845   0.08120   0.07371  -0.0222   0.0504   1.0000
  15.000   1.2774   0.08518   0.07770  -0.0223   0.0475   1.0000
  15.250   1.2755   0.08871   0.08140  -0.0225   0.0447   1.0000
  15.500   1.2735   0.09221   0.08501  -0.0227   0.0425   1.0000
  15.750   1.2725   0.09552   0.08839  -0.0228   0.0409   1.0000
  16.000   1.2735   0.09839   0.09126  -0.0226   0.0395   1.0000
  16.250   1.2778   0.10076   0.09374  -0.0219   0.0384   1.0000
  16.500   1.2800   0.10377   0.09694  -0.0218   0.0375   1.0000
  16.750   1.2807   0.10712   0.10048  -0.0219   0.0368   1.0000
  17.000   1.2792   0.11096   0.10451  -0.0224   0.0363   1.0000
  17.250   1.2747   0.11545   0.10920  -0.0235   0.0360   1.0000
  17.500   1.2669   0.12065   0.11461  -0.0253   0.0358   1.0000
  17.750   1.2550   0.12684   0.12102  -0.0280   0.0358   1.0000
  18.000   1.2391   0.13410   0.12852  -0.0317   0.0359   1.0000
  18.250   1.2189   0.14271   0.13735  -0.0367   0.0362   1.0000
  18.500   1.1939   0.15307   0.14793  -0.0431   0.0367   1.0000
  18.750   1.1636   0.16568   0.16071  -0.0512   0.0375   1.0000
  19.000   1.1329   0.17973   0.17482  -0.0600   0.0384   1.0000
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