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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 50,000
Max Cl/Cd: 38.57 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe144-il-50000.txt
Download as CSV file: xf-goe144-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3361   0.11308   0.10610  -0.0216   1.0000   0.1440
  -8.500  -0.3427   0.11247   0.10561  -0.0226   1.0000   0.1470
  -8.250  -0.3569   0.11299   0.10629  -0.0234   1.0000   0.1479
  -8.000  -0.3306   0.10514   0.09836  -0.0217   1.0000   0.1531
  -7.750  -0.3297   0.10283   0.09614  -0.0213   1.0000   0.1576
  -7.500  -0.3418   0.10240   0.09586  -0.0212   1.0000   0.1608
  -7.250  -0.3573   0.10293   0.09657  -0.0233   1.0000   0.1620
  -7.000  -0.3362   0.09594   0.08956  -0.0193   1.0000   0.1669
  -6.750  -0.3367   0.09371   0.08742  -0.0190   1.0000   0.1724
  -6.500  -0.3478   0.09388   0.08773  -0.0229   1.0000   0.1760
  -6.250  -0.3361   0.08850   0.08239  -0.0186   1.0000   0.1813
  -6.000  -0.3373   0.08686   0.08083  -0.0198   1.0000   0.1889
  -5.500  -0.3315   0.08148   0.07558  -0.0198   1.0000   0.2034
  -5.000  -0.3204   0.07678   0.07092  -0.0237   1.0000   0.2198
  -4.750  -0.3158   0.07260   0.06684  -0.0196   1.0000   0.2244
  -4.500  -0.3055   0.07022   0.06444  -0.0229   1.0000   0.2358
  -4.250  -0.2940   0.06772   0.06189  -0.0247   1.0000   0.2494
  -3.500  -0.2699   0.05874   0.05303  -0.0212   1.0000   0.2957
  -3.250  -0.2569   0.05628   0.05055  -0.0224   1.0000   0.3212
  -3.000  -0.2507   0.05353   0.04787  -0.0198   1.0000   0.3415
  -2.750  -0.2448   0.05122   0.04561  -0.0180   1.0000   0.3807
  -2.500  -0.2463   0.04908   0.04359  -0.0130   1.0000   0.4264
  -2.250  -0.2463   0.04722   0.04178  -0.0085   1.0000   0.4805
  -2.000  -0.0880   0.04050   0.03304  -0.0479   1.0000   0.2213
  -1.750  -0.0623   0.03818   0.03045  -0.0494   1.0000   0.2139
  -1.500  -0.0352   0.03620   0.02807  -0.0511   1.0000   0.2120
  -1.250  -0.0088   0.03443   0.02586  -0.0524   1.0000   0.2122
  -1.000   0.0135   0.03327   0.02438  -0.0530   1.0000   0.2241
  -0.750   0.0529   0.03236   0.02315  -0.0565   0.9923   0.2539
  -0.500   0.1040   0.03156   0.02204  -0.0620   0.9781   0.2858
  -0.250   0.1551   0.03094   0.02103  -0.0671   0.9633   0.2985
   0.000   0.2038   0.03055   0.02033  -0.0716   0.9484   0.3155
   0.250   0.2558   0.03025   0.01969  -0.0765   0.9336   0.3307
   0.500   0.3057   0.02985   0.01917  -0.0809   0.9192   0.3543
   0.750   0.3523   0.02944   0.01882  -0.0846   0.9049   0.3935
   1.000   0.3961   0.02892   0.01866  -0.0878   0.8906   0.4492
   1.250   0.4413   0.02761   0.01860  -0.0909   0.8763   1.0000
   1.500   0.4840   0.02810   0.01865  -0.0934   0.8610   1.0000
   1.750   0.5253   0.02847   0.01873  -0.0955   0.8459   1.0000
   2.000   0.5667   0.02870   0.01879  -0.0976   0.8309   1.0000
   2.250   0.6097   0.02878   0.01875  -0.0996   0.8159   1.0000
   2.500   0.6512   0.02874   0.01864  -0.1012   0.8009   1.0000
   2.750   0.6857   0.02885   0.01872  -0.1016   0.7848   1.0000
   3.000   0.7175   0.02903   0.01888  -0.1015   0.7685   1.0000
   3.250   0.7510   0.02913   0.01899  -0.1016   0.7529   1.0000
   3.500   0.7839   0.02926   0.01914  -0.1015   0.7374   1.0000
   3.750   0.8158   0.02945   0.01940  -0.1013   0.7218   1.0000
   4.000   0.8461   0.02975   0.01975  -0.1008   0.7061   1.0000
   4.250   0.8756   0.03010   0.02015  -0.1002   0.6900   1.0000
   4.500   0.9042   0.03052   0.02068  -0.0994   0.6739   1.0000
   4.750   0.9325   0.03098   0.02122  -0.0986   0.6576   1.0000
   5.000   0.9607   0.03146   0.02177  -0.0977   0.6413   1.0000
   5.250   0.9830   0.03233   0.02275  -0.0963   0.6240   1.0000
   5.500   1.0013   0.03344   0.02404  -0.0947   0.6058   1.0000
   5.750   1.0251   0.03407   0.02478  -0.0931   0.5872   1.0000
   6.000   1.0593   0.03358   0.02431  -0.0917   0.5668   1.0000
   6.250   1.0775   0.03405   0.02490  -0.0892   0.5432   1.0000
   6.500   1.1061   0.03380   0.02472  -0.0873   0.5213   1.0000
   6.750   1.1252   0.03453   0.02562  -0.0853   0.5007   1.0000
   7.000   1.1508   0.03486   0.02607  -0.0838   0.4817   1.0000
   7.250   1.1720   0.03547   0.02684  -0.0819   0.4616   1.0000
   7.500   1.1972   0.03452   0.02587  -0.0793   0.4331   1.0000
   7.750   1.2174   0.03361   0.02500  -0.0764   0.4029   1.0000
   8.000   1.2353   0.03298   0.02438  -0.0735   0.3747   1.0000
   8.250   1.2525   0.03274   0.02419  -0.0708   0.3495   1.0000
   8.500   1.2631   0.03275   0.02432  -0.0675   0.3217   1.0000
   8.750   1.2691   0.03297   0.02461  -0.0637   0.2901   1.0000
   9.000   1.2664   0.03362   0.02515  -0.0592   0.2497   1.0000
   9.250   1.2577   0.03529   0.02671  -0.0545   0.2016   1.0000
   9.500   1.2440   0.03776   0.02884  -0.0496   0.1569   1.0000
   9.750   1.2325   0.04066   0.03135  -0.0455   0.1304   1.0000
  10.000   1.2279   0.04364   0.03405  -0.0424   0.1142   1.0000
  10.250   1.2350   0.04641   0.03675  -0.0401   0.1018   1.0000
  10.500   1.2528   0.04912   0.03955  -0.0384   0.0919   1.0000
  10.750   1.2745   0.05195   0.04234  -0.0374   0.0838   1.0000
  11.000   1.2884   0.05486   0.04557  -0.0359   0.0787   1.0000
  11.250   1.3120   0.05832   0.04918  -0.0354   0.0752   1.0000
  11.500   1.3347   0.06307   0.05411  -0.0353   0.0732   1.0000
  11.750   1.3305   0.06688   0.05836  -0.0331   0.0729   1.0000
  12.000   1.3213   0.07092   0.06275  -0.0311   0.0728   1.0000
  12.250   1.3090   0.07519   0.06733  -0.0296   0.0728   1.0000
  12.500   1.2938   0.07980   0.07222  -0.0288   0.0730   1.0000
  12.750   1.2766   0.08481   0.07748  -0.0288   0.0732   1.0000
  13.250   1.2091   0.09768   0.09093  -0.0343   0.0751   1.0000
  13.500   1.1293   0.11391   0.10750  -0.0473   0.0796   1.0000
  13.750   1.0918   0.12709   0.12072  -0.0558   0.0828   1.0000
  14.000   1.0736   0.13720   0.13080  -0.0613   0.0846   1.0000
  14.250   1.0643   0.14563   0.13920  -0.0653   0.0856   1.0000
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