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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 50,000
Max Cl/Cd: 28.15 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe140-il-50000.txt
Download as CSV file: xf-goe140-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2301   0.10666   0.10057  -0.0262   1.0000   0.1170
  -8.500  -0.2405   0.10612   0.10015  -0.0277   1.0000   0.1179
  -8.250  -0.3023   0.10900   0.10251  -0.0197   1.0000   0.1137
  -8.000  -0.3055   0.10781   0.10143  -0.0215   1.0000   0.1166
  -7.750  -0.3132   0.10779   0.10155  -0.0253   1.0000   0.1178
  -7.500  -0.2992   0.10167   0.09548  -0.0225   1.0000   0.1208
  -7.250  -0.2914   0.09829   0.09215  -0.0220   1.0000   0.1254
  -7.000  -0.2909   0.09641   0.09038  -0.0239   1.0000   0.1301
  -6.750  -0.2949   0.09653   0.09062  -0.0307   1.0000   0.1325
  -6.500  -0.2849   0.09072   0.08489  -0.0243   1.0000   0.1378
  -6.250  -0.2837   0.08877   0.08303  -0.0256   1.0000   0.1442
  -6.000  -0.2840   0.08732   0.08168  -0.0296   1.0000   0.1477
  -5.750  -0.2812   0.08365   0.07811  -0.0248   1.0000   0.1530
  -5.500  -0.2799   0.08271   0.07720  -0.0289   1.0000   0.1604
  -5.250  -0.2799   0.07952   0.07410  -0.0265   1.0000   0.1638
  -5.000  -0.2789   0.07731   0.07195  -0.0248   1.0000   0.1706
  -4.500  -0.2716   0.07310   0.06782  -0.0261   1.0000   0.1870
  -4.250  -0.2673   0.07067   0.06544  -0.0263   1.0000   0.1952
  -4.000  -0.2597   0.06855   0.06333  -0.0276   1.0000   0.2088
  -3.750  -0.2539   0.06643   0.06126  -0.0275   1.0000   0.2249
  -3.500  -0.2462   0.06468   0.05953  -0.0280   1.0000   0.2486
  -3.250   0.1208   0.03739   0.03185  -0.0296   1.0000   1.0000
  -3.000   0.1158   0.03711   0.03173  -0.0276   1.0000   1.0000
  -2.500  -0.1680   0.05305   0.04828  -0.0222   0.9602   0.5059
  -2.250  -0.1535   0.05033   0.04567  -0.0159   0.9455   0.5900
  -2.000  -0.1403   0.04763   0.04307  -0.0087   0.9308   0.6655
  -1.750  -0.1244   0.04474   0.04026  -0.0014   0.9164   0.7328
  -1.500  -0.0840   0.04182   0.03730  -0.0046   0.8999   0.7723
  -1.250   0.3026   0.03617   0.02802  -0.1080   0.8727   0.2666
  -1.000   0.3599   0.03414   0.02548  -0.1121   0.8556   0.2310
  -0.750   0.4120   0.03280   0.02352  -0.1145   0.8382   0.2031
  -0.500   0.4562   0.03160   0.02186  -0.1155   0.8208   0.1887
  -0.250   0.4877   0.03078   0.02079  -0.1150   0.7997   0.1823
   0.000   0.5202   0.03008   0.01980  -0.1143   0.7807   0.1798
   0.250   0.5516   0.02941   0.01888  -0.1133   0.7628   0.1849
   0.500   0.5819   0.02889   0.01808  -0.1120   0.7456   0.1883
   0.750   0.6091   0.02853   0.01756  -0.1107   0.7282   0.1916
   1.000   0.6346   0.02828   0.01726  -0.1095   0.7108   0.1992
   1.250   0.6609   0.02806   0.01700  -0.1085   0.6946   0.2182
   1.500   0.6881   0.02775   0.01687  -0.1079   0.6796   0.2593
   1.750   0.7105   0.02630   0.01682  -0.1055   0.6667   1.0000
   2.000   0.7381   0.02678   0.01676  -0.1043   0.6536   1.0000
   2.250   0.7639   0.02742   0.01705  -0.1034   0.6403   1.0000
   2.500   0.7882   0.02827   0.01771  -0.1029   0.6270   1.0000
   2.750   0.8121   0.02919   0.01848  -0.1025   0.6145   1.0000
   3.000   0.8362   0.03014   0.01931  -0.1020   0.6033   1.0000
   3.250   0.8637   0.03068   0.01967  -0.1015   0.5946   1.0000
   3.500   0.8844   0.03215   0.02118  -0.1013   0.5834   1.0000
   3.750   0.9069   0.03340   0.02240  -0.1011   0.5741   1.0000
   4.000   0.9320   0.03430   0.02323  -0.1007   0.5660   1.0000
   4.250   0.9496   0.03626   0.02528  -0.1006   0.5570   1.0000
   4.500   0.9744   0.03732   0.02635  -0.1003   0.5508   1.0000
   4.750   0.9873   0.04001   0.02919  -0.1005   0.5434   1.0000
   5.000   1.0067   0.04180   0.03103  -0.1004   0.5373   1.0000
   5.250   1.0227   0.04406   0.03337  -0.1003   0.5316   1.0000
   5.500   1.0232   0.04820   0.03768  -0.1005   0.5248   1.0000
   5.750   1.0437   0.04997   0.03953  -0.1003   0.5207   1.0000
   6.000   1.0351   0.05547   0.04517  -0.1009   0.5173   1.0000
   6.250   0.9907   0.06525   0.05503  -0.1030   0.5167   1.0000
   6.500   0.9688   0.07191   0.06172  -0.1041   0.5179   1.0000
   6.750   0.7549   0.09720   0.08720  -0.1163   0.6963   1.0000
   7.000   0.7669   0.09959   0.08960  -0.1161   0.6880   1.0000
   7.250   0.7867   0.10293   0.09294  -0.1171   0.6836   1.0000
   7.500   0.7916   0.10483   0.09486  -0.1159   0.6723   1.0000
   7.750   0.7951   0.10713   0.09721  -0.1149   0.6630   1.0000
   8.000   0.8206   0.11046   0.10058  -0.1162   0.6558   1.0000
   8.250   0.8169   0.11236   0.10251  -0.1146   0.6459   1.0000
   8.500   0.8516   0.11667   0.10691  -0.1168   0.6396   1.0000
   8.750   0.8496   0.11821   0.10849  -0.1151   0.6264   1.0000
   9.000   0.8554   0.12047   0.11080  -0.1142   0.6129   1.0000
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