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GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il)
Reynolds number: 200,000
Max Cl/Cd: 64.39 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe289-il-200000-n5.txt
Download as CSV file: xf-goe289-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 289 (MVA 289) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2841   0.04623   0.04163  -0.1406   0.9145   0.0342
 -10.750  -0.3013   0.03884   0.03376  -0.1516   0.8958   0.0342
 -10.500  -0.3114   0.03593   0.03047  -0.1517   0.8795   0.0343
 -10.250  -0.3120   0.03376   0.02799  -0.1507   0.8655   0.0345
 -10.000  -0.3018   0.03202   0.02610  -0.1499   0.8540   0.0348
  -9.750  -0.2889   0.03048   0.02436  -0.1493   0.8429   0.0351
  -9.500  -0.2770   0.02925   0.02298  -0.1479   0.8310   0.0354
  -9.250  -0.2629   0.02793   0.02145  -0.1468   0.8202   0.0356
  -9.000  -0.2465   0.02675   0.02007  -0.1458   0.8098   0.0359
  -8.750  -0.2301   0.02568   0.01881  -0.1446   0.7993   0.0361
  -8.500  -0.2109   0.02467   0.01759  -0.1437   0.7902   0.0364
  -8.250  -0.1922   0.02376   0.01652  -0.1426   0.7803   0.0367
  -8.000  -0.1717   0.02291   0.01548  -0.1418   0.7716   0.0371
  -7.750  -0.1512   0.02213   0.01454  -0.1408   0.7626   0.0375
  -7.500  -0.1294   0.02140   0.01364  -0.1400   0.7547   0.0379
  -7.250  -0.1081   0.02076   0.01286  -0.1390   0.7461   0.0383
  -7.000  -0.0852   0.02015   0.01209  -0.1383   0.7386   0.0387
  -6.750  -0.0634   0.01964   0.01145  -0.1373   0.7304   0.0393
  -6.500  -0.0404   0.01910   0.01079  -0.1366   0.7232   0.0399
  -6.250  -0.0191   0.01857   0.01023  -0.1356   0.7154   0.0407
  -6.000   0.0036   0.01813   0.00971  -0.1347   0.7079   0.0414
  -5.750   0.0267   0.01773   0.00923  -0.1339   0.7009   0.0422
  -5.500   0.0493   0.01736   0.00879  -0.1330   0.6931   0.0429
  -5.250   0.0733   0.01702   0.00832  -0.1323   0.6863   0.0438
  -5.000   0.0959   0.01670   0.00794  -0.1313   0.6784   0.0447
  -4.750   0.1196   0.01640   0.00755  -0.1305   0.6711   0.0457
  -4.500   0.1428   0.01610   0.00719  -0.1296   0.6638   0.0471
  -4.250   0.1663   0.01584   0.00688  -0.1288   0.6558   0.0489
  -4.000   0.1905   0.01562   0.00656  -0.1280   0.6488   0.0515
  -3.750   0.2135   0.01535   0.00631  -0.1271   0.6406   0.0563
  -3.500   0.2374   0.01511   0.00606  -0.1263   0.6333   0.0664
  -3.250   0.2606   0.01490   0.00592  -0.1254   0.6251   0.0854
  -3.000   0.2848   0.01477   0.00578  -0.1247   0.6174   0.1023
  -2.750   0.3088   0.01469   0.00567  -0.1239   0.6096   0.1151
  -2.500   0.3331   0.01464   0.00556  -0.1231   0.6016   0.1263
  -2.250   0.3572   0.01457   0.00547  -0.1224   0.5943   0.1383
  -2.000   0.3810   0.01449   0.00537  -0.1216   0.5868   0.1489
  -1.750   0.4051   0.01444   0.00527  -0.1208   0.5801   0.1605
  -1.500   0.4286   0.01437   0.00520  -0.1200   0.5727   0.1730
  -1.250   0.4522   0.01430   0.00512  -0.1192   0.5659   0.1880
  -0.750   0.4979   0.01408   0.00509  -0.1174   0.5523   0.2524
  -0.500   0.5209   0.01402   0.00513  -0.1165   0.5464   0.3036
  -0.250   0.5441   0.01402   0.00519  -0.1156   0.5398   0.3400
   0.000   0.5673   0.01406   0.00521  -0.1146   0.5333   0.3657
   0.250   0.5907   0.01411   0.00523  -0.1137   0.5273   0.3880
   0.500   0.6134   0.01412   0.00527  -0.1127   0.5208   0.4090
   0.750   0.6360   0.01416   0.00530  -0.1117   0.5151   0.4289
   1.000   0.6585   0.01417   0.00536  -0.1107   0.5097   0.4518
   1.250   0.6801   0.01416   0.00544  -0.1095   0.5037   0.4824
   1.500   0.7005   0.01411   0.00553  -0.1081   0.4982   0.5337
   1.750   0.7192   0.01393   0.00567  -0.1062   0.4928   0.6455
   2.250   0.8408   0.01397   0.00615  -0.1203   0.4782   1.0000
   2.500   0.8613   0.01413   0.00628  -0.1189   0.4726   1.0000
   2.750   0.8816   0.01432   0.00639  -0.1175   0.4672   1.0000
   3.000   0.9016   0.01453   0.00650  -0.1160   0.4623   1.0000
   3.250   0.9218   0.01472   0.00666  -0.1146   0.4569   1.0000
   3.500   0.9412   0.01492   0.00681  -0.1131   0.4513   1.0000
   3.750   0.9601   0.01515   0.00696  -0.1115   0.4462   1.0000
   4.000   0.9786   0.01537   0.00714  -0.1098   0.4410   1.0000
   4.250   0.9963   0.01558   0.00733  -0.1080   0.4357   1.0000
   4.500   1.0140   0.01583   0.00752  -0.1062   0.4309   1.0000
   4.750   1.0323   0.01609   0.00772  -0.1045   0.4265   1.0000
   5.000   1.0507   0.01633   0.00798  -0.1029   0.4217   1.0000
   5.250   1.0688   0.01660   0.00822  -0.1013   0.4170   1.0000
   5.500   1.0867   0.01690   0.00846  -0.0996   0.4128   1.0000
   5.750   1.1051   0.01720   0.00875  -0.0981   0.4083   1.0000
   6.000   1.1230   0.01750   0.00907  -0.0966   0.4035   1.0000
   6.250   1.1406   0.01783   0.00937  -0.0950   0.3992   1.0000
   6.500   1.1586   0.01819   0.00967  -0.0935   0.3954   1.0000
   6.750   1.1771   0.01853   0.01005  -0.0922   0.3915   1.0000
   7.000   1.1952   0.01889   0.01044  -0.0908   0.3876   1.0000
   7.250   1.2129   0.01928   0.01083  -0.0894   0.3839   1.0000
   7.500   1.2308   0.01969   0.01121  -0.0881   0.3806   1.0000
   7.750   1.2493   0.02010   0.01162  -0.0869   0.3776   1.0000
   8.000   1.2667   0.02053   0.01211  -0.0856   0.3741   1.0000
   8.250   1.2839   0.02098   0.01260  -0.0843   0.3707   1.0000
   8.500   1.3009   0.02145   0.01309  -0.0830   0.3673   1.0000
   8.750   1.3181   0.02194   0.01356  -0.0817   0.3643   1.0000
   9.000   1.3362   0.02243   0.01405  -0.0806   0.3614   1.0000
   9.250   1.3525   0.02297   0.01468  -0.0794   0.3586   1.0000
   9.500   1.3687   0.02352   0.01531  -0.0781   0.3557   1.0000
   9.750   1.3849   0.02410   0.01593  -0.0769   0.3530   1.0000
  10.000   1.4017   0.02466   0.01653  -0.0758   0.3504   1.0000
  10.250   1.4195   0.02522   0.01710  -0.0748   0.3481   1.0000
  10.500   1.4384   0.02576   0.01764  -0.0740   0.3457   1.0000
  10.750   1.4486   0.02657   0.01859  -0.0723   0.3421   1.0000
  11.000   1.4581   0.02742   0.01954  -0.0705   0.3378   1.0000
  11.250   1.4687   0.02824   0.02038  -0.0689   0.3333   1.0000
  11.500   1.4797   0.02909   0.02122  -0.0674   0.3285   1.0000
  11.750   1.4853   0.03024   0.02252  -0.0656   0.3237   1.0000
  12.000   1.4922   0.03137   0.02370  -0.0639   0.3186   1.0000
  12.250   1.5022   0.03235   0.02465  -0.0626   0.3140   1.0000
  12.500   1.5073   0.03374   0.02619  -0.0610   0.3094   1.0000
  12.750   1.5128   0.03514   0.02770  -0.0596   0.3045   1.0000
  13.000   1.5192   0.03649   0.02907  -0.0583   0.2998   1.0000
  13.250   1.5256   0.03794   0.03060  -0.0571   0.2957   1.0000
  13.500   1.5279   0.03979   0.03260  -0.0559   0.2900   1.0000
  13.750   1.5310   0.04157   0.03442  -0.0547   0.2846   1.0000
  14.000   1.5330   0.04357   0.03651  -0.0537   0.2791   1.0000
  14.250   1.5330   0.04583   0.03889  -0.0527   0.2730   1.0000
  14.500   1.5324   0.04815   0.04124  -0.0517   0.2667   1.0000
  14.750   1.5303   0.05081   0.04405  -0.0510   0.2597   1.0000
  15.000   1.5251   0.05378   0.04706  -0.0502   0.2517   1.0000
  15.250   1.5175   0.05721   0.05060  -0.0496   0.2414   1.0000
  15.500   1.5090   0.06079   0.05425  -0.0492   0.2310   1.0000
  15.750   1.4964   0.06494   0.05844  -0.0488   0.2178   1.0000
  16.000   1.4809   0.06954   0.06305  -0.0486   0.2028   1.0000
  16.250   1.4582   0.07513   0.06861  -0.0485   0.1848   1.0000
  16.500   1.4290   0.08167   0.07509  -0.0488   0.1647   1.0000
  16.750   1.3993   0.08852   0.08190  -0.0493   0.1460   1.0000
  17.000   1.3658   0.09608   0.08941  -0.0502   0.1257   1.0000
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