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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.18 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe124-il-1000000.txt
Download as CSV file: xf-goe124-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2941   0.09079   0.08917  -0.0270   0.9362   0.0168
  -7.750  -0.2917   0.08753   0.08583  -0.0299   0.9084   0.0169
  -7.500  -0.2797   0.08339   0.08162  -0.0355   0.8892   0.0169
  -7.250  -0.2709   0.07929   0.07746  -0.0367   0.8743   0.0171
  -7.000  -0.2577   0.07667   0.07478  -0.0379   0.8599   0.0173
  -6.750  -0.2420   0.07397   0.07201  -0.0404   0.8456   0.0175
  -5.250  -0.0833   0.04837   0.04580  -0.0771   0.7670   0.0209
  -5.000  -0.0603   0.04618   0.04353  -0.0789   0.7546   0.0211
  -4.750  -0.0343   0.04388   0.04115  -0.0813   0.7432   0.0214
  -4.500  -0.0060   0.04149   0.03866  -0.0841   0.7325   0.0220
  -4.000   0.0739   0.03355   0.03025  -0.0933   0.7126   0.0248
  -3.750   0.1072   0.03002   0.02647  -0.0960   0.7029   0.0249
  -3.500   0.1368   0.02551   0.02173  -0.0992   0.6936   0.0255
  -3.250   0.1648   0.02426   0.02039  -0.1002   0.6848   0.0259
  -3.000   0.1940   0.02287   0.01887  -0.1013   0.6765   0.0264
  -2.750   0.2245   0.02132   0.01716  -0.1024   0.6688   0.0275
  -2.500   0.2585   0.02036   0.01586  -0.1026   0.6610   0.0300
  -2.250   0.2897   0.01906   0.01432  -0.1034   0.6539   0.0301
  -2.000   0.3204   0.01778   0.01281  -0.1042   0.6467   0.0302
   0.250   0.5902   0.00981   0.00371  -0.1086   0.5841   0.0346
   0.500   0.6200   0.00920   0.00304  -0.1088   0.5772   0.0330
   0.750   0.6493   0.00888   0.00268  -0.1090   0.5691   0.0329
   1.000   0.6785   0.00868   0.00247  -0.1092   0.5598   0.0335
   1.250   0.7075   0.00857   0.00232  -0.1094   0.5495   0.0343
   1.500   0.7366   0.00847   0.00219  -0.1096   0.5395   0.0349
   1.750   0.7656   0.00840   0.00210  -0.1098   0.5283   0.0355
   2.000   0.7943   0.00839   0.00205  -0.1100   0.5138   0.0362
   2.250   0.8230   0.00839   0.00199  -0.1102   0.4984   0.0374
   2.500   0.8518   0.00837   0.00191  -0.1104   0.4845   0.0397
   2.750   0.8803   0.00843   0.00194  -0.1105   0.4689   0.0423
   3.000   0.9085   0.00854   0.00198  -0.1106   0.4519   0.0450
   3.250   0.9399   0.00740   0.00233  -0.1123   0.4327   0.8100
   3.500   0.9602   0.00721   0.00237  -0.1104   0.4141   1.0000
   3.750   0.9879   0.00744   0.00249  -0.1104   0.3949   1.0000
   4.000   1.0156   0.00767   0.00263  -0.1105   0.3786   1.0000
   4.250   1.0433   0.00788   0.00277  -0.1105   0.3660   1.0000
   4.500   1.0708   0.00810   0.00294  -0.1106   0.3540   1.0000
   4.750   1.0984   0.00829   0.00309  -0.1106   0.3440   1.0000
   5.000   1.1260   0.00848   0.00325  -0.1106   0.3352   1.0000
   5.250   1.1534   0.00870   0.00343  -0.1106   0.3261   1.0000
   5.500   1.1809   0.00888   0.00359  -0.1106   0.3176   1.0000
   5.750   1.2080   0.00911   0.00378  -0.1106   0.3071   1.0000
   6.000   1.2348   0.00937   0.00399  -0.1106   0.2943   1.0000
   6.250   1.2617   0.00960   0.00419  -0.1105   0.2809   1.0000
   6.500   1.2881   0.00989   0.00441  -0.1105   0.2625   1.0000
   6.750   1.3126   0.01045   0.00475  -0.1102   0.2202   1.0000
   7.000   1.3318   0.01173   0.00557  -0.1093   0.1435   1.0000
   7.250   1.3557   0.01231   0.00604  -0.1088   0.1244   1.0000
   7.500   1.3803   0.01275   0.00643  -0.1085   0.1138   1.0000
   7.750   1.4053   0.01310   0.00678  -0.1082   0.1059   1.0000
   8.000   1.4296   0.01354   0.00718  -0.1078   0.0972   1.0000
   8.250   1.4545   0.01386   0.00751  -0.1075   0.0910   1.0000
   8.500   1.4784   0.01430   0.00791  -0.1071   0.0817   1.0000
   8.750   1.5009   0.01486   0.00838  -0.1065   0.0665   1.0000
   9.000   1.5195   0.01583   0.00915  -0.1054   0.0417   1.0000
   9.250   1.5356   0.01699   0.01014  -0.1039   0.0213   1.0000
   9.500   1.5547   0.01777   0.01093  -0.1028   0.0174   1.0000
   9.750   1.5753   0.01835   0.01156  -0.1018   0.0163   1.0000
  10.000   1.5939   0.01906   0.01231  -0.1006   0.0151   1.0000
  10.250   1.6092   0.02002   0.01333  -0.0989   0.0137   1.0000
  10.500   1.6276   0.02063   0.01400  -0.0977   0.0132   1.0000
  10.750   1.6438   0.02135   0.01477  -0.0962   0.0126   1.0000
  11.000   1.6575   0.02214   0.01563  -0.0943   0.0121   1.0000
  11.250   1.6667   0.02303   0.01658  -0.0917   0.0117   1.0000
  11.500   1.6722   0.02418   0.01780  -0.0888   0.0112   1.0000
  11.750   1.6728   0.02582   0.01955  -0.0857   0.0108   1.0000
  12.000   1.6761   0.02745   0.02128  -0.0833   0.0105   1.0000
  12.250   1.6843   0.02880   0.02271  -0.0818   0.0103   1.0000
  12.500   1.6913   0.03035   0.02435  -0.0803   0.0101   1.0000
  12.750   1.6967   0.03213   0.02622  -0.0789   0.0099   1.0000
  13.000   1.7013   0.03409   0.02827  -0.0777   0.0096   1.0000
  13.250   1.7054   0.03616   0.03042  -0.0767   0.0093   1.0000
  13.500   1.7085   0.03844   0.03278  -0.0758   0.0091   1.0000
  13.750   1.7104   0.04091   0.03534  -0.0750   0.0089   1.0000
  14.000   1.7100   0.04371   0.03823  -0.0744   0.0087   1.0000
  14.250   1.7063   0.04699   0.04160  -0.0739   0.0085   1.0000
  14.500   1.6985   0.05081   0.04553  -0.0735   0.0084   1.0000
  14.750   1.6863   0.05527   0.05012  -0.0733   0.0082   1.0000
  15.000   1.6716   0.06018   0.05516  -0.0733   0.0081   1.0000
  15.250   1.6591   0.06499   0.06009  -0.0735   0.0080   1.0000
  15.500   1.6553   0.06879   0.06400  -0.0738   0.0079   1.0000
  15.750   1.6514   0.07268   0.06799  -0.0743   0.0079   1.0000
  16.000   1.6457   0.07689   0.07231  -0.0749   0.0078   1.0000
  16.250   1.6390   0.08135   0.07687  -0.0757   0.0077   1.0000
  16.500   1.6321   0.08594   0.08156  -0.0767   0.0076   1.0000
  16.750   1.6241   0.09074   0.08647  -0.0778   0.0075   1.0000
  17.000   1.6152   0.09571   0.09156  -0.0790   0.0075   1.0000
  17.250   1.6067   0.10074   0.09669  -0.0804   0.0074   1.0000
  17.500   1.5982   0.10585   0.10190  -0.0819   0.0073   1.0000
  17.750   1.5892   0.11106   0.10722  -0.0835   0.0072   1.0000
  18.000   1.5804   0.11629   0.11255  -0.0853   0.0071   1.0000
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