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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 50,000
Max Cl/Cd: 43.75 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe164-il-50000-n5.txt
Download as CSV file: xf-goe164-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 164 (MVA MK.10) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2778   0.10955   0.10356  -0.0238   1.0000   0.1006
  -7.000  -0.2906   0.10924   0.10341  -0.0230   1.0000   0.1015
  -6.750  -0.2992   0.10841   0.10272  -0.0234   1.0000   0.1019
  -6.500  -0.3050   0.10717   0.10161  -0.0241   1.0000   0.1021
  -6.250  -0.3043   0.10376   0.09830  -0.0218   1.0000   0.1026
  -6.000  -0.3045   0.10090   0.09550  -0.0197   1.0000   0.1032
  -5.500  -0.2461   0.08808   0.08250  -0.0411   0.9854   0.0622
  -5.250  -0.2241   0.08389   0.07829  -0.0426   0.9785   0.0611
  -5.000  -0.1968   0.07949   0.07383  -0.0477   0.9701   0.0599
  -4.750  -0.1663   0.07491   0.06919  -0.0540   0.9614   0.0579
  -4.500  -0.1275   0.06960   0.06379  -0.0629   0.9539   0.0557
  -4.250  -0.0904   0.06433   0.05840  -0.0714   0.9440   0.0544
  -4.000  -0.0453   0.05890   0.05281  -0.0813   0.9362   0.0561
  -3.750   0.0088   0.05235   0.04598  -0.0934   0.9289   0.0585
  -3.250   0.1361   0.03693   0.02924  -0.1196   0.9193   0.0656
  -3.000   0.1903   0.03253   0.02398  -0.1269   0.9143   0.0732
  -2.750   0.2300   0.03105   0.02220  -0.1299   0.9063   0.0854
  -2.500   0.2712   0.02968   0.02050  -0.1327   0.8987   0.0996
  -2.250   0.3062   0.02920   0.01986  -0.1341   0.8886   0.1189
  -2.000   0.3458   0.02871   0.01917  -0.1359   0.8797   0.1491
  -1.750   0.3856   0.02825   0.01834  -0.1378   0.8696   0.1900
  -1.500   0.4205   0.02803   0.01802  -0.1386   0.8570   0.2224
  -1.250   0.4563   0.02771   0.01763  -0.1394   0.8441   0.2549
  -1.000   0.4949   0.02693   0.01658  -0.1408   0.8316   0.2696
  -0.750   0.5341   0.02623   0.01548  -0.1422   0.8196   0.2792
  -0.500   0.5736   0.02559   0.01462  -0.1437   0.8099   0.2882
  -0.250   0.6068   0.02525   0.01400  -0.1442   0.7971   0.2949
   0.000   0.6394   0.02494   0.01356  -0.1447   0.7846   0.3018
   0.250   0.6725   0.02469   0.01312  -0.1451   0.7722   0.3115
   0.500   0.7050   0.02444   0.01276  -0.1455   0.7594   0.3207
   0.750   0.7371   0.02422   0.01242  -0.1458   0.7465   0.3295
   1.000   0.7684   0.02405   0.01216  -0.1459   0.7332   0.3412
   1.250   0.7964   0.02399   0.01206  -0.1455   0.7186   0.3556
   1.500   0.8239   0.02393   0.01201  -0.1451   0.7038   0.3718
   1.750   0.8510   0.02386   0.01197  -0.1446   0.6889   0.3912
   2.000   0.8776   0.02375   0.01198  -0.1441   0.6740   0.4216
   2.250   0.9030   0.02341   0.01208  -0.1435   0.6590   0.4972
   2.500   0.9253   0.02296   0.01201  -0.1418   0.6434   1.0000
   2.750   0.9517   0.02322   0.01206  -0.1411   0.6275   1.0000
   3.000   0.9777   0.02350   0.01219  -0.1404   0.6116   1.0000
   3.250   1.0025   0.02383   0.01237  -0.1395   0.5952   1.0000
   3.500   1.0269   0.02417   0.01261  -0.1386   0.5785   1.0000
   3.750   1.0512   0.02454   0.01289  -0.1376   0.5620   1.0000
   4.000   1.0753   0.02492   0.01319  -0.1367   0.5460   1.0000
   4.250   1.0996   0.02534   0.01353  -0.1359   0.5310   1.0000
   4.500   1.1237   0.02579   0.01394  -0.1351   0.5167   1.0000
   4.750   1.1478   0.02626   0.01435  -0.1342   0.5031   1.0000
   5.000   1.1712   0.02677   0.01484  -0.1333   0.4899   1.0000
   5.250   1.1933   0.02733   0.01543  -0.1323   0.4766   1.0000
   5.500   1.2152   0.02792   0.01608  -0.1313   0.4639   1.0000
   5.750   1.2373   0.02851   0.01671  -0.1303   0.4523   1.0000
   6.000   1.2607   0.02908   0.01729  -0.1295   0.4423   1.0000
   6.250   1.2820   0.02974   0.01809  -0.1284   0.4316   1.0000
   6.500   1.3026   0.03044   0.01888  -0.1273   0.4210   1.0000
   6.750   1.3242   0.03107   0.01956  -0.1262   0.4110   1.0000
   7.000   1.3448   0.03174   0.02032  -0.1250   0.4008   1.0000
   7.250   1.3635   0.03253   0.02125  -0.1236   0.3904   1.0000
   7.500   1.3840   0.03324   0.02208  -0.1225   0.3809   1.0000
   7.750   1.4032   0.03402   0.02299  -0.1211   0.3712   1.0000
   8.000   1.4208   0.03492   0.02407  -0.1197   0.3617   1.0000
   8.250   1.4427   0.03564   0.02485  -0.1187   0.3535   1.0000
   8.500   1.4573   0.03677   0.02626  -0.1169   0.3446   1.0000
   9.000   1.4929   0.03888   0.02886  -0.1142   0.3298   1.0000
   9.250   1.5141   0.03985   0.03000  -0.1133   0.3234   1.0000
   9.500   1.5268   0.04124   0.03171  -0.1114   0.3166   1.0000
   9.750   1.5423   0.04239   0.03312  -0.1098   0.3095   1.0000
  10.000   1.5490   0.04364   0.03462  -0.1071   0.3003   1.0000
  10.250   1.5513   0.04446   0.03557  -0.1035   0.2884   1.0000
  10.500   1.5462   0.04543   0.03664  -0.0992   0.2759   1.0000
  10.750   1.5347   0.04729   0.03885  -0.0951   0.2646   1.0000
  11.000   1.5252   0.04933   0.04112  -0.0916   0.2535   1.0000
  11.250   1.5161   0.05162   0.04361  -0.0888   0.2425   1.0000
  11.500   1.5057   0.05432   0.04650  -0.0866   0.2307   1.0000
  11.750   1.4944   0.05749   0.04985  -0.0851   0.2180   1.0000
  12.000   1.4837   0.06099   0.05350  -0.0841   0.2051   1.0000
  12.250   1.4724   0.06480   0.05740  -0.0835   0.1916   1.0000
  12.500   1.4594   0.06907   0.06168  -0.0833   0.1774   1.0000
  12.750   1.4457   0.07373   0.06635  -0.0835   0.1645   1.0000
  13.000   1.4290   0.07938   0.07219  -0.0843   0.1516   1.0000
  13.250   1.4102   0.08593   0.07905  -0.0860   0.1381   1.0000
  13.500   1.3894   0.09330   0.08681  -0.0883   0.1246   1.0000
  13.750   1.3720   0.09911   0.09224  -0.0898   0.0938   1.0000
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