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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 50,000
Max Cl/Cd: 36.12 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe142-il-50000.txt
Download as CSV file: xf-goe142-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3980   0.10788   0.10113  -0.0097   1.0000   0.1220
  -7.750  -0.4032   0.10724   0.10062  -0.0131   1.0000   0.1244
  -7.500  -0.3956   0.10295   0.09640  -0.0137   1.0000   0.1266
  -7.250  -0.3838   0.09859   0.09206  -0.0124   1.0000   0.1323
  -7.000  -0.3808   0.09665   0.09020  -0.0163   1.0000   0.1375
  -6.750  -0.3752   0.09371   0.08734  -0.0199   1.0000   0.1403
  -6.500  -0.3643   0.08940   0.08303  -0.0174   1.0000   0.1468
  -6.250  -0.3579   0.08878   0.08243  -0.0271   1.0000   0.1532
  -6.000  -0.3488   0.08317   0.07692  -0.0209   1.0000   0.1589
  -5.750  -0.3392   0.08151   0.07528  -0.0281   1.0000   0.1677
  -5.500  -0.3315   0.07707   0.07093  -0.0235   1.0000   0.1754
  -5.250  -0.3225   0.07403   0.06793  -0.0252   1.0000   0.1855
  -5.000  -0.3129   0.07106   0.06500  -0.0262   1.0000   0.1989
  -4.750  -0.3037   0.06802   0.06202  -0.0259   1.0000   0.2146
  -4.500  -0.2900   0.06584   0.05979  -0.0295   1.0000   0.2384
  -4.250  -0.2838   0.06223   0.05629  -0.0262   1.0000   0.2554
  -4.000  -0.2736   0.05947   0.05356  -0.0260   1.0000   0.2825
  -3.750  -0.2665   0.05656   0.05071  -0.0235   1.0000   0.3124
  -3.500  -0.2616   0.05392   0.04815  -0.0204   1.0000   0.3545
  -3.250  -0.2612   0.05132   0.04570  -0.0146   1.0000   0.4021
  -3.000  -0.2636   0.04886   0.04339  -0.0077   1.0000   0.4584
  -2.750  -0.2664   0.04645   0.04113  -0.0005   1.0000   0.5142
  -2.500  -0.2695   0.04411   0.03893   0.0070   1.0000   0.5698
  -2.250  -0.2717   0.04173   0.03668   0.0146   1.0000   0.6183
  -2.000  -0.2657   0.03923   0.03425   0.0186   1.0000   0.6572
  -1.750  -0.0049   0.03337   0.02512  -0.0527   1.0000   0.2068
  -1.500   0.0293   0.03119   0.02247  -0.0542   1.0000   0.1884
  -1.250   0.0631   0.02934   0.02007  -0.0552   1.0000   0.1730
  -1.000   0.0953   0.02803   0.01814  -0.0557   1.0000   0.1668
  -0.750   0.1228   0.02674   0.01672  -0.0563   1.0000   0.1775
  -0.500   0.1518   0.02588   0.01541  -0.0566   1.0000   0.1815
  -0.250   0.1778   0.02500   0.01443  -0.0567   1.0000   0.1922
   0.000   0.2042   0.02448   0.01373  -0.0569   1.0000   0.2120
   0.250   0.2306   0.02401   0.01321  -0.0571   1.0000   0.2302
   0.500   0.2571   0.02363   0.01296  -0.0578   1.0000   0.2714
   0.750   0.2882   0.02119   0.01266  -0.0587   1.0000   0.7933
   1.000   0.3053   0.02207   0.01284  -0.0582   0.9966   1.0000
   1.250   0.3729   0.02305   0.01326  -0.0668   0.9735   1.0000
   1.500   0.4339   0.02379   0.01374  -0.0739   0.9486   1.0000
   1.750   0.4923   0.02429   0.01410  -0.0800   0.9233   1.0000
   2.000   0.5529   0.02447   0.01423  -0.0857   0.8990   1.0000
   2.250   0.6021   0.02451   0.01426  -0.0889   0.8729   1.0000
   2.500   0.6443   0.02445   0.01421  -0.0904   0.8466   1.0000
   2.750   0.6825   0.02432   0.01410  -0.0907   0.8206   1.0000
   3.000   0.7174   0.02415   0.01397  -0.0902   0.7948   1.0000
   3.250   0.7497   0.02395   0.01377  -0.0890   0.7693   1.0000
   3.500   0.7798   0.02378   0.01359  -0.0874   0.7439   1.0000
   3.750   0.8058   0.02387   0.01372  -0.0854   0.7166   1.0000
   4.000   0.8311   0.02406   0.01389  -0.0835   0.6893   1.0000
   4.250   0.8558   0.02436   0.01417  -0.0816   0.6621   1.0000
   4.500   0.8802   0.02476   0.01455  -0.0799   0.6355   1.0000
   4.750   0.9045   0.02524   0.01502  -0.0782   0.6096   1.0000
   5.000   0.9293   0.02575   0.01556  -0.0766   0.5852   1.0000
   5.250   0.9535   0.02640   0.01620  -0.0752   0.5610   1.0000
   5.500   0.9766   0.02727   0.01714  -0.0740   0.5370   1.0000
   5.750   1.0016   0.02798   0.01782  -0.0726   0.5159   1.0000
   6.000   1.0238   0.02907   0.01911  -0.0715   0.4936   1.0000
   6.250   1.0488   0.02991   0.01995  -0.0703   0.4743   1.0000
   6.500   1.0699   0.03123   0.02149  -0.0693   0.4537   1.0000
   6.750   1.0930   0.03234   0.02271  -0.0682   0.4348   1.0000
   7.000   1.1166   0.03343   0.02387  -0.0670   0.4165   1.0000
   7.250   1.1360   0.03497   0.02576  -0.0658   0.3971   1.0000
   7.500   1.1587   0.03600   0.02689  -0.0644   0.3773   1.0000
   7.750   1.1781   0.03723   0.02833  -0.0628   0.3555   1.0000
   8.000   1.1997   0.03769   0.02882  -0.0609   0.3295   1.0000
   8.250   1.2180   0.03789   0.02906  -0.0586   0.2978   1.0000
   8.500   1.2358   0.03762   0.02866  -0.0560   0.2599   1.0000
   8.750   1.2460   0.03812   0.02906  -0.0529   0.2154   1.0000
   9.000   1.2547   0.03984   0.03059  -0.0497   0.1735   1.0000
   9.250   1.2640   0.04189   0.03253  -0.0472   0.1444   1.0000
   9.500   1.2807   0.04463   0.03500  -0.0455   0.1259   1.0000
   9.750   1.2928   0.04753   0.03805  -0.0437   0.1127   1.0000
  10.000   1.2982   0.05106   0.04219  -0.0414   0.1047   1.0000
  10.250   1.3111   0.05509   0.04633  -0.0400   0.0993   1.0000
  10.500   1.3067   0.05978   0.05167  -0.0376   0.0972   1.0000
  10.750   1.2971   0.06447   0.05687  -0.0354   0.0957   1.0000
  11.000   1.2820   0.06922   0.06201  -0.0334   0.0949   1.0000
  11.250   1.2598   0.07398   0.06707  -0.0316   0.0953   1.0000
  11.500   1.2341   0.07926   0.07259  -0.0310   0.0963   1.0000
  11.750   1.2081   0.08533   0.07882  -0.0322   0.0976   1.0000
  12.000   1.1837   0.09214   0.08575  -0.0347   0.0988   1.0000
  12.250   1.1620   0.09957   0.09326  -0.0381   0.0997   1.0000
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