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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 100,000
Max Cl/Cd: 62.58 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe164-il-100000-n5.txt
Download as CSV file: xf-goe164-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2691   0.10694   0.10253  -0.0261   1.0000   0.0462
  -7.500  -0.2817   0.10634   0.10205  -0.0246   1.0000   0.0468
  -7.250  -0.2886   0.10524   0.10105  -0.0253   0.9978   0.0472
  -7.000  -0.2602   0.10067   0.09647  -0.0353   0.9897   0.0476
  -6.750  -0.2334   0.09585   0.09164  -0.0431   0.9822   0.0477
  -6.250  -0.1971   0.08455   0.08031  -0.0462   0.9711   0.0338
  -6.000  -0.1723   0.08001   0.07576  -0.0525   0.9628   0.0335
  -5.500  -0.1200   0.07076   0.06645  -0.0654   0.9437   0.0323
  -5.250  -0.0919   0.06577   0.06143  -0.0723   0.9334   0.0310
  -5.000  -0.0533   0.05962   0.05519  -0.0823   0.9260   0.0299
  -4.750  -0.0166   0.05328   0.04875  -0.0918   0.9146   0.0294
  -4.500   0.0305   0.04632   0.04160  -0.1032   0.9067   0.0303
  -4.250   0.1129   0.03041   0.02462  -0.1278   0.9026   0.0324
  -4.000   0.1641   0.02524   0.01840  -0.1352   0.8982   0.0344
  -3.750   0.2007   0.02295   0.01565  -0.1376   0.8892   0.0378
  -3.500   0.2408   0.02137   0.01378  -0.1401   0.8826   0.0431
  -3.250   0.2768   0.02003   0.01206  -0.1416   0.8717   0.0485
  -3.000   0.3155   0.01876   0.01061  -0.1437   0.8616   0.0581
  -2.750   0.3562   0.01767   0.00935  -0.1460   0.8523   0.0725
  -2.500   0.3951   0.01692   0.00866  -0.1479   0.8411   0.0986
  -2.250   0.4323   0.01682   0.00847  -0.1492   0.8284   0.1428
  -2.000   0.4690   0.01700   0.00838  -0.1503   0.8143   0.1711
  -1.500   0.5371   0.01712   0.00810  -0.1521   0.7859   0.2061
  -1.250   0.5688   0.01711   0.00793  -0.1526   0.7727   0.2198
  -1.000   0.5997   0.01695   0.00767  -0.1529   0.7596   0.2262
  -0.750   0.6301   0.01679   0.00731  -0.1532   0.7460   0.2310
  -0.500   0.6592   0.01667   0.00706  -0.1532   0.7320   0.2359
  -0.250   0.6874   0.01658   0.00687  -0.1530   0.7175   0.2408
   0.250   0.7418   0.01646   0.00653  -0.1522   0.6868   0.2501
   0.500   0.7679   0.01643   0.00645  -0.1516   0.6707   0.2554
   0.750   0.7942   0.01645   0.00636  -0.1511   0.6545   0.2626
   1.000   0.8202   0.01645   0.00634  -0.1504   0.6382   0.2696
   1.250   0.8460   0.01650   0.00631  -0.1498   0.6219   0.2777
   1.500   0.8716   0.01655   0.00632  -0.1492   0.6050   0.2857
   1.750   0.8969   0.01663   0.00635  -0.1484   0.5876   0.2964
   2.000   0.9219   0.01674   0.00643  -0.1477   0.5699   0.3110
   2.250   0.9467   0.01686   0.00652  -0.1470   0.5523   0.3301
   2.500   0.9713   0.01700   0.00664  -0.1462   0.5351   0.3580
   2.750   0.9958   0.01709   0.00680  -0.1455   0.5183   0.4038
   3.250   1.0397   0.01669   0.00710  -0.1429   0.4858   1.0000
   3.500   1.0636   0.01702   0.00733  -0.1420   0.4691   1.0000
   3.750   1.0870   0.01737   0.00756  -0.1411   0.4521   1.0000
   4.000   1.1101   0.01774   0.00782  -0.1402   0.4353   1.0000
   4.250   1.1332   0.01812   0.00813  -0.1393   0.4202   1.0000
   4.500   1.1563   0.01851   0.00845  -0.1384   0.4074   1.0000
   4.750   1.1793   0.01891   0.00879  -0.1375   0.3960   1.0000
   5.000   1.2020   0.01934   0.00916  -0.1366   0.3851   1.0000
   5.250   1.2250   0.01975   0.00960  -0.1357   0.3752   1.0000
   5.500   1.2476   0.02020   0.01002  -0.1348   0.3668   1.0000
   5.750   1.2702   0.02065   0.01049  -0.1339   0.3579   1.0000
   6.000   1.2925   0.02112   0.01100  -0.1330   0.3498   1.0000
   6.250   1.3146   0.02159   0.01152  -0.1320   0.3418   1.0000
   6.500   1.3367   0.02209   0.01205  -0.1310   0.3350   1.0000
   6.750   1.3587   0.02258   0.01263  -0.1301   0.3279   1.0000
   7.000   1.3799   0.02313   0.01321  -0.1290   0.3215   1.0000
   7.250   1.4015   0.02362   0.01389  -0.1280   0.3141   1.0000
   7.500   1.4218   0.02419   0.01452  -0.1268   0.3073   1.0000
   7.750   1.4425   0.02472   0.01521  -0.1257   0.2998   1.0000
   8.000   1.4620   0.02530   0.01590  -0.1244   0.2928   1.0000
   8.250   1.4816   0.02587   0.01664  -0.1231   0.2854   1.0000
   8.500   1.4988   0.02648   0.01739  -0.1214   0.2766   1.0000
   8.750   1.5136   0.02705   0.01811  -0.1194   0.2629   1.0000
   9.000   1.5263   0.02767   0.01884  -0.1171   0.2456   1.0000
   9.250   1.5358   0.02838   0.01960  -0.1143   0.2246   1.0000
   9.500   1.5421   0.02935   0.02050  -0.1113   0.2023   1.0000
   9.750   1.5470   0.03054   0.02164  -0.1082   0.1858   1.0000
  10.000   1.5496   0.03200   0.02305  -0.1050   0.1702   1.0000
  10.250   1.5497   0.03374   0.02475  -0.1018   0.1514   1.0000
  10.500   1.5528   0.03542   0.02650  -0.0991   0.0976   1.0000
  10.750   1.5358   0.03876   0.02945  -0.0951   0.0803   1.0000
  11.000   1.5316   0.04130   0.03213  -0.0924   0.0608   1.0000
  11.250   1.5175   0.04491   0.03562  -0.0897   0.0352   1.0000
  11.500   1.5071   0.04845   0.03919  -0.0878   0.0297   1.0000
  11.750   1.4970   0.05220   0.04307  -0.0864   0.0269   1.0000
  12.000   1.4856   0.05634   0.04738  -0.0855   0.0253   1.0000
  12.250   1.4764   0.06045   0.05169  -0.0851   0.0243   1.0000
  12.500   1.4656   0.06497   0.05644  -0.0851   0.0235   1.0000
  12.750   1.4533   0.06991   0.06160  -0.0855   0.0229   1.0000
  13.000   1.4396   0.07532   0.06722  -0.0863   0.0223   1.0000
  13.250   1.4248   0.08114   0.07326  -0.0875   0.0219   1.0000
  13.500   1.4094   0.08726   0.07958  -0.0891   0.0216   1.0000
  13.750   1.3936   0.09367   0.08617  -0.0909   0.0212   1.0000
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