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GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il)
Reynolds number: 100,000
Max Cl/Cd: 46.47 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe289-il-100000-n5.txt
Download as CSV file: xf-goe289-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0645   0.09829   0.09306  -0.0947   0.9293   0.0544
 -10.000  -0.0552   0.09369   0.08843  -0.0989   0.9213   0.0541
  -9.750  -0.0675   0.08381   0.07851  -0.1074   0.9140   0.0516
  -9.500  -0.0596   0.07910   0.07376  -0.1115   0.9050   0.0514
  -9.250  -0.0517   0.07383   0.06846  -0.1167   0.8967   0.0511
  -9.000  -0.0573   0.06761   0.06222  -0.1215   0.8845   0.0508
  -8.750  -0.1280   0.05136   0.04580  -0.1348   0.8643   0.0496
  -8.500  -0.1730   0.04361   0.03753  -0.1375   0.8474   0.0491
  -8.250  -0.1833   0.03955   0.03301  -0.1369   0.8356   0.0492
  -8.000  -0.1780   0.03641   0.02939  -0.1366   0.8268   0.0498
  -7.750  -0.1719   0.03423   0.02682  -0.1350   0.8162   0.0505
  -7.500  -0.1551   0.03193   0.02401  -0.1347   0.8091   0.0514
  -7.250  -0.1406   0.03063   0.02251  -0.1332   0.7993   0.0521
  -7.000  -0.1158   0.02941   0.02114  -0.1333   0.7927   0.0529
  -6.750  -0.0975   0.02838   0.01995  -0.1321   0.7837   0.0535
  -6.500  -0.0730   0.02726   0.01863  -0.1319   0.7767   0.0543
  -6.250  -0.0516   0.02634   0.01754  -0.1310   0.7686   0.0553
  -6.000  -0.0278   0.02541   0.01642  -0.1304   0.7610   0.0564
  -5.750  -0.0031   0.02456   0.01536  -0.1300   0.7539   0.0577
  -5.500   0.0190   0.02387   0.01455  -0.1290   0.7455   0.0590
  -5.250   0.0474   0.02324   0.01383  -0.1292   0.7395   0.0613
  -5.000   0.0669   0.02283   0.01336  -0.1278   0.7304   0.0640
  -4.750   0.0937   0.02225   0.01264  -0.1276   0.7236   0.0673
  -4.500   0.1155   0.02186   0.01223  -0.1265   0.7154   0.0707
  -4.250   0.1401   0.02140   0.01165  -0.1259   0.7080   0.0757
  -4.000   0.1650   0.02100   0.01122  -0.1253   0.7008   0.0832
  -3.750   0.1871   0.02069   0.01089  -0.1242   0.6925   0.0945
  -3.500   0.2156   0.02038   0.01050  -0.1243   0.6863   0.1124
  -3.250   0.2359   0.02027   0.01038  -0.1229   0.6773   0.1274
  -3.000   0.2626   0.02008   0.01007  -0.1226   0.6703   0.1421
  -2.750   0.2853   0.01997   0.00991  -0.1217   0.6624   0.1567
  -2.500   0.3093   0.01980   0.00973  -0.1210   0.6547   0.1732
  -2.250   0.3343   0.01962   0.00953  -0.1205   0.6478   0.1920
  -2.000   0.3558   0.01948   0.00945  -0.1193   0.6395   0.2102
  -1.750   0.3826   0.01924   0.00922  -0.1191   0.6332   0.2305
  -1.500   0.4024   0.01916   0.00922  -0.1176   0.6248   0.2513
  -1.250   0.4276   0.01901   0.00909  -0.1170   0.6180   0.2815
  -1.000   0.4503   0.01896   0.00910  -0.1160   0.6106   0.3177
  -0.750   0.4738   0.01893   0.00908  -0.1152   0.6033   0.3549
  -0.500   0.5002   0.01887   0.00896  -0.1148   0.5973   0.3895
  -0.250   0.5215   0.01888   0.00902  -0.1136   0.5894   0.4184
   0.000   0.5483   0.01878   0.00892  -0.1133   0.5833   0.4502
   0.500   0.5942   0.01868   0.00903  -0.1114   0.5694   0.5322
   0.750   0.6199   0.01848   0.00900  -0.1108   0.5639   0.6142
   1.000   0.6438   0.01824   0.00924  -0.1098   0.5565   0.7560
   1.500   0.7482   0.01846   0.00936  -0.1198   0.5419   1.0000
   1.750   0.7691   0.01868   0.00945  -0.1186   0.5355   1.0000
   2.250   0.8117   0.01916   0.00968  -0.1163   0.5233   1.0000
   2.500   0.8334   0.01940   0.00981  -0.1152   0.5174   1.0000
   2.750   0.8583   0.01961   0.00986  -0.1147   0.5124   1.0000
   3.000   0.8750   0.01995   0.01018  -0.1128   0.5056   1.0000
   3.250   0.8963   0.02020   0.01034  -0.1117   0.4997   1.0000
   3.500   0.9204   0.02045   0.01046  -0.1111   0.4947   1.0000
   3.750   0.9364   0.02082   0.01083  -0.1091   0.4882   1.0000
   4.000   0.9573   0.02112   0.01105  -0.1079   0.4828   1.0000
   4.500   0.9972   0.02180   0.01165  -0.1055   0.4726   1.0000
   4.750   1.0161   0.02215   0.01196  -0.1040   0.4672   1.0000
   5.000   1.0398   0.02242   0.01214  -0.1034   0.4627   1.0000
   5.250   1.0554   0.02286   0.01258  -0.1015   0.4574   1.0000
   5.500   1.0702   0.02327   0.01300  -0.0994   0.4519   1.0000
   5.750   1.0908   0.02361   0.01328  -0.0983   0.4475   1.0000
   6.000   1.1134   0.02396   0.01358  -0.0976   0.4436   1.0000
   6.250   1.1237   0.02453   0.01422  -0.0949   0.4387   1.0000
   6.500   1.1398   0.02500   0.01470  -0.0932   0.4342   1.0000
   6.750   1.1611   0.02538   0.01503  -0.0923   0.4303   1.0000
   7.000   1.1818   0.02580   0.01543  -0.0914   0.4266   1.0000
   7.250   1.1898   0.02651   0.01622  -0.0886   0.4218   1.0000
   7.500   1.2047   0.02706   0.01680  -0.0869   0.4175   1.0000
   7.750   1.2255   0.02749   0.01722  -0.0861   0.4140   1.0000
   8.000   1.2503   0.02787   0.01755  -0.0859   0.4111   1.0000
   8.250   1.2548   0.02882   0.01864  -0.0829   0.4071   1.0000
   8.500   1.2653   0.02964   0.01953  -0.0808   0.4032   1.0000
   8.750   1.2816   0.03028   0.02022  -0.0795   0.4000   1.0000
   9.000   1.3035   0.03073   0.02066  -0.0790   0.3970   1.0000
   9.250   1.3247   0.03126   0.02120  -0.0784   0.3942   1.0000
   9.500   1.3212   0.03266   0.02277  -0.0749   0.3901   1.0000
   9.750   1.3272   0.03379   0.02401  -0.0727   0.3865   1.0000
  10.000   1.3411   0.03463   0.02490  -0.0714   0.3835   1.0000
  10.250   1.3620   0.03520   0.02550  -0.0709   0.3810   1.0000
  10.500   1.3888   0.03556   0.02587  -0.0710   0.3790   1.0000
  10.750   1.3776   0.03765   0.02816  -0.0674   0.3755   1.0000
  11.000   1.3648   0.04003   0.03072  -0.0641   0.3716   1.0000
  11.250   1.3666   0.04172   0.03251  -0.0622   0.3683   1.0000
  11.500   1.3821   0.04260   0.03345  -0.0613   0.3657   1.0000
  11.750   1.4072   0.04294   0.03383  -0.0612   0.3637   1.0000
  12.000   1.4261   0.04374   0.03469  -0.0607   0.3617   1.0000
  12.250   1.2945   0.05640   0.04775  -0.0532   0.3522   1.0000
  12.500   1.3009   0.05830   0.04973  -0.0525   0.3494   1.0000
  12.750   1.3271   0.05825   0.04975  -0.0522   0.3479   1.0000
  13.000   1.3591   0.05772   0.04926  -0.0521   0.3467   1.0000
  13.500   1.0156   0.10982   0.10171  -0.0562   0.3024   1.0000
  13.750   1.0316   0.11082   0.10278  -0.0559   0.3006   1.0000
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