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GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il)
Reynolds number: 100,000
Max Cl/Cd: 38.61 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe289-il-100000.txt
Download as CSV file: xf-goe289-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1607   0.12784   0.12329  -0.0589   0.9737   0.1153
 -10.250  -0.1585   0.12536   0.12081  -0.0661   0.9674   0.1201
 -10.000  -0.1680   0.12264   0.11813  -0.0744   0.9590   0.1215
  -9.750  -0.1186   0.11582   0.11123  -0.0747   0.9572   0.1235
  -9.500  -0.0951   0.11218   0.10757  -0.0766   0.9496   0.1262
  -9.250  -0.0734   0.10839   0.10375  -0.0811   0.9445   0.1304
  -9.000  -0.0916   0.10698   0.10238  -0.0890   0.9329   0.1358
  -8.750  -0.0637   0.10115   0.09653  -0.0923   0.9292   0.1380
  -8.500  -0.0203   0.09671   0.09203  -0.0946   0.9271   0.1422
  -8.250  -0.0080   0.09386   0.08918  -0.0969   0.9176   0.1467
  -8.000  -0.0540   0.09313   0.08853  -0.1060   0.9009   0.1525
  -7.750   0.0024   0.08644   0.08177  -0.1074   0.9013   0.1548
  -7.500   0.0419   0.08246   0.07774  -0.1102   0.8977   0.1585
  -7.250   0.0648   0.07861   0.07384  -0.1161   0.8929   0.1652
  -7.000  -0.0164   0.07824   0.07354  -0.1189   0.8661   0.1700
  -6.750   0.0325   0.07380   0.06909  -0.1177   0.8641   0.1719
  -6.500  -0.0573   0.05657   0.05131  -0.1277   0.8442   0.1064
  -6.250  -0.0885   0.04879   0.04292  -0.1262   0.8315   0.0959
  -6.000  -0.0723   0.04437   0.03794  -0.1273   0.8253   0.0942
  -5.750  -0.0657   0.04201   0.03525  -0.1253   0.8155   0.0942
  -5.500  -0.0440   0.03902   0.03172  -0.1254   0.8090   0.0947
  -5.250  -0.0089   0.03576   0.02799  -0.1273   0.8057   0.0954
  -5.000  -0.0035   0.03478   0.02688  -0.1239   0.7939   0.0962
  -4.750   0.0354   0.03273   0.02461  -0.1258   0.7900   0.0985
  -4.500   0.0502   0.03198   0.02371  -0.1236   0.7801   0.1005
  -4.250   0.0842   0.03046   0.02184  -0.1243   0.7746   0.1053
  -4.000   0.1272   0.02885   0.02011  -0.1266   0.7712   0.1126
  -3.750   0.1367   0.02867   0.01982  -0.1233   0.7597   0.1180
  -3.500   0.1769   0.02718   0.01825  -0.1249   0.7553   0.1314
  -3.250   0.1931   0.02673   0.01778  -0.1228   0.7461   0.1492
  -3.000   0.2237   0.02577   0.01688  -0.1229   0.7397   0.1818
  -2.750   0.2659   0.02477   0.01585  -0.1250   0.7358   0.2109
  -2.500   0.2732   0.02508   0.01618  -0.1215   0.7243   0.2257
  -2.250   0.3125   0.02455   0.01561  -0.1231   0.7194   0.2565
  -2.000   0.3244   0.02486   0.01597  -0.1204   0.7094   0.2753
  -1.750   0.3581   0.02438   0.01557  -0.1210   0.7034   0.2996
  -1.500   0.3835   0.02424   0.01544  -0.1203   0.6962   0.3239
  -1.250   0.4043   0.02415   0.01543  -0.1188   0.6878   0.3540
  -1.000   0.4426   0.02337   0.01473  -0.1201   0.6831   0.4132
  -0.750   0.4494   0.02360   0.01518  -0.1165   0.6730   0.4583
  -0.500   0.4825   0.02294   0.01473  -0.1168   0.6674   0.5257
  -0.250   0.5023   0.02293   0.01492  -0.1151   0.6597   0.5863
   0.000   0.5259   0.02262   0.01493  -0.1139   0.6522   0.6746
   0.250   0.6593   0.02141   0.01396  -0.1333   0.6462   1.0000
   0.500   0.6653   0.02203   0.01447  -0.1297   0.6367   1.0000
   0.750   0.7001   0.02192   0.01407  -0.1307   0.6313   1.0000
   1.000   0.7093   0.02251   0.01459  -0.1276   0.6225   1.0000
   1.250   0.7378   0.02255   0.01443  -0.1275   0.6161   1.0000
   1.500   0.7626   0.02277   0.01449  -0.1269   0.6096   1.0000
   1.750   0.7767   0.02326   0.01490  -0.1246   0.6016   1.0000
   2.000   0.8130   0.02315   0.01458  -0.1258   0.5966   1.0000
   2.250   0.8202   0.02389   0.01532  -0.1224   0.5882   1.0000
   2.500   0.8490   0.02397   0.01525  -0.1224   0.5820   1.0000
   2.750   0.8772   0.02416   0.01529  -0.1224   0.5762   1.0000
   3.000   0.8868   0.02483   0.01597  -0.1194   0.5681   1.0000
   3.250   0.9219   0.02481   0.01578  -0.1205   0.5631   1.0000
   3.500   0.9327   0.02559   0.01658  -0.1178   0.5562   1.0000
   3.750   0.9522   0.02604   0.01698  -0.1165   0.5496   1.0000
   4.000   0.9911   0.02597   0.01673  -0.1182   0.5451   1.0000
   4.250   0.9914   0.02706   0.01791  -0.1139   0.5375   1.0000
   4.500   1.0156   0.02740   0.01818  -0.1133   0.5317   1.0000
   4.750   1.0563   0.02736   0.01796  -0.1154   0.5276   1.0000
   5.000   1.0479   0.02881   0.01958  -0.1099   0.5204   1.0000
   5.250   1.0678   0.02938   0.02012  -0.1088   0.5151   1.0000
   5.500   1.1072   0.02940   0.02001  -0.1106   0.5113   1.0000
   5.750   1.1010   0.03091   0.02165  -0.1057   0.5051   1.0000
   6.000   1.1081   0.03190   0.02268  -0.1028   0.4993   1.0000
   6.250   1.1451   0.03194   0.02264  -0.1042   0.4954   1.0000
   6.500   1.1728   0.03248   0.02314  -0.1044   0.4917   1.0000
   6.750   1.1177   0.03573   0.02664  -0.0930   0.4845   1.0000
   7.000   1.1379   0.03641   0.02733  -0.0921   0.4805   1.0000
   7.250   1.1847   0.03629   0.02714  -0.0950   0.4777   1.0000
   7.500   0.9239   0.05571   0.04700  -0.0702   0.4575   1.0000
   7.750   0.9822   0.05265   0.04388  -0.0709   0.4578   1.0000
   8.000   1.0478   0.04948   0.04067  -0.0727   0.4581   1.0000
   8.250   1.1307   0.04584   0.03697  -0.0767   0.4585   1.0000
   9.500   0.6109   0.12096   0.11287  -0.0720   0.4686   1.0000
   9.750   0.6254   0.12296   0.11488  -0.0720   0.4642   1.0000
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