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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 100,000
Max Cl/Cd: 53.4 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe165-il-100000-n5.txt
Download as CSV file: xf-goe165-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 165 (MVA MK.11) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3049   0.09443   0.09013  -0.0352   1.0000   0.0261
  -7.750  -0.3085   0.09214   0.08792  -0.0339   1.0000   0.0256
  -7.500  -0.3158   0.08987   0.08575  -0.0323   1.0000   0.0252
  -7.250  -0.3270   0.08776   0.08375  -0.0304   1.0000   0.0249
  -7.000  -0.3212   0.08354   0.07959  -0.0339   0.9959   0.0245
  -6.750  -0.2998   0.07688   0.07295  -0.0430   0.9880   0.0241
  -6.500  -0.2770   0.06883   0.06490  -0.0542   0.9787   0.0235
  -6.250  -0.2469   0.05605   0.05197  -0.0746   0.9675   0.0223
  -5.750  -0.1420   0.03576   0.03012  -0.1149   0.9481   0.0215
  -5.500  -0.0949   0.03138   0.02505  -0.1220   0.9431   0.0211
  -5.250  -0.0568   0.02846   0.02160  -0.1253   0.9339   0.0210
  -5.000  -0.0143   0.02603   0.01882  -0.1286   0.9279   0.0213
  -4.750   0.0207   0.02425   0.01685  -0.1300   0.9167   0.0218
  -4.500   0.0571   0.02286   0.01533  -0.1314   0.9059   0.0236
  -4.250   0.0959   0.02172   0.01408  -0.1330   0.8961   0.0259
  -4.000   0.1345   0.02072   0.01296  -0.1349   0.8840   0.0274
  -3.750   0.1749   0.01974   0.01181  -0.1376   0.8708   0.0304
  -3.500   0.2168   0.01882   0.01066  -0.1407   0.8576   0.0384
  -3.250   0.2608   0.01754   0.00909  -0.1443   0.8441   0.0596
  -3.000   0.3033   0.01628   0.00875  -0.1482   0.8295   0.2939
  -2.750   0.3404   0.01653   0.00876  -0.1494   0.8122   0.3374
  -2.250   0.4107   0.01708   0.00885  -0.1510   0.7753   0.3712
  -2.000   0.4447   0.01712   0.00858  -0.1519   0.7581   0.3814
  -1.750   0.4759   0.01734   0.00866  -0.1521   0.7426   0.3902
  -1.500   0.5066   0.01752   0.00867  -0.1523   0.7276   0.3999
  -1.250   0.5374   0.01763   0.00855  -0.1527   0.7133   0.4098
  -1.000   0.5663   0.01772   0.00854  -0.1527   0.6996   0.4147
  -0.750   0.5952   0.01778   0.00845  -0.1527   0.6857   0.4204
  -0.500   0.6240   0.01783   0.00831  -0.1528   0.6713   0.4267
  -0.250   0.6510   0.01792   0.00832  -0.1525   0.6564   0.4310
   0.000   0.6781   0.01800   0.00827  -0.1522   0.6409   0.4365
   0.250   0.7050   0.01806   0.00821  -0.1519   0.6246   0.4418
   0.500   0.7306   0.01814   0.00825  -0.1513   0.6077   0.4457
   0.750   0.7562   0.01822   0.00826  -0.1508   0.5889   0.4507
   1.000   0.7819   0.01831   0.00824  -0.1503   0.5673   0.4562
   1.250   0.8063   0.01839   0.00829  -0.1495   0.5412   0.4598
   1.500   0.8307   0.01852   0.00830  -0.1488   0.5113   0.4639
   1.750   0.8549   0.01871   0.00829  -0.1480   0.4829   0.4684
   2.250   0.9030   0.01923   0.00848  -0.1466   0.4452   0.4748
   2.500   0.9276   0.01951   0.00867  -0.1460   0.4327   0.4784
   2.750   0.9528   0.01981   0.00888  -0.1456   0.4218   0.4823
   3.000   0.9777   0.02015   0.00913  -0.1451   0.4111   0.4857
   3.500   1.0261   0.02079   0.00970  -0.1439   0.3892   0.4917
   3.750   1.0506   0.02112   0.01001  -0.1434   0.3790   0.4955
   4.000   1.0748   0.02150   0.01030  -0.1428   0.3697   0.4992
   4.250   1.0994   0.02175   0.01063  -0.1423   0.3609   0.5021
   4.500   1.1234   0.02210   0.01097  -0.1417   0.3537   0.5051
   4.750   1.1481   0.02237   0.01134  -0.1411   0.3467   0.5087
   5.000   1.1726   0.02271   0.01171  -0.1406   0.3416   0.5128
   5.250   1.1972   0.02304   0.01211  -0.1401   0.3369   0.5166
   5.500   1.2215   0.02332   0.01257  -0.1395   0.3317   0.5206
   5.750   1.2454   0.02367   0.01299  -0.1389   0.3266   0.5249
   6.000   1.2691   0.02403   0.01344  -0.1382   0.3214   0.5291
   6.250   1.2892   0.02431   0.01381  -0.1370   0.3098   0.5328
   6.500   1.3071   0.02458   0.01415  -0.1353   0.2923   0.5372
   6.750   1.3263   0.02488   0.01459  -0.1339   0.2753   0.5425
   7.000   1.3457   0.02520   0.01502  -0.1326   0.2568   0.5478
   7.250   1.3648   0.02560   0.01550  -0.1313   0.2364   0.5539
   7.500   1.3790   0.02633   0.01605  -0.1293   0.1885   0.5600
   7.750   1.3738   0.02895   0.01783  -0.1250   0.1039   0.5644
   8.000   1.3763   0.03085   0.01951  -0.1216   0.0563   0.5701
   8.250   1.3867   0.03192   0.02074  -0.1191   0.0466   0.5773
   8.500   1.4000   0.03277   0.02180  -0.1170   0.0240   0.5869
   8.750   1.4019   0.03449   0.02353  -0.1138   0.0209   0.5974
   9.000   1.4084   0.03584   0.02508  -0.1111   0.0190   0.6148
   9.250   1.4131   0.03700   0.02677  -0.1083   0.0178   0.7084
   9.500   1.4116   0.03846   0.02850  -0.1048   0.0172   1.0000
   9.750   1.4127   0.04044   0.03070  -0.1022   0.0164   1.0000
  10.000   1.4114   0.04273   0.03321  -0.0999   0.0157   1.0000
  10.250   1.4081   0.04536   0.03607  -0.0979   0.0151   1.0000
  10.500   1.4028   0.04839   0.03932  -0.0963   0.0147   1.0000
  10.750   1.3960   0.05183   0.04299  -0.0953   0.0145   1.0000
  11.000   1.3869   0.05584   0.04723  -0.0948   0.0143   1.0000
  11.250   1.3761   0.06036   0.05197  -0.0949   0.0141   1.0000
  11.500   1.3635   0.06539   0.05722  -0.0954   0.0140   1.0000
  11.750   1.3491   0.07090   0.06294  -0.0964   0.0140   1.0000
  12.000   1.3335   0.07684   0.06908  -0.0977   0.0139   1.0000
  12.250   1.3175   0.08312   0.07555  -0.0994   0.0139   1.0000
  12.500   1.3024   0.08948   0.08209  -0.1013   0.0139   1.0000
  12.750   1.2887   0.09574   0.08852  -0.1031   0.0138   1.0000
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