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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 100,000
Max Cl/Cd: 44.91 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe422-il-100000.txt
Download as CSV file: xf-goe422-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 422 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0528   0.10724   0.10235  -0.0873   0.9134   0.1215
  -8.000  -0.0690   0.10586   0.10101  -0.0897   0.9046   0.1254
  -7.750  -0.1238   0.10572   0.10094  -0.0939   0.8912   0.1266
  -7.500  -0.0414   0.09874   0.09391  -0.0934   0.8947   0.1300
  -7.250  -0.0442   0.09756   0.09276  -0.0904   0.8851   0.1324
  -7.000  -0.0391   0.09497   0.09018  -0.0927   0.8793   0.1374
  -6.750  -0.0807   0.09471   0.08999  -0.0912   0.8652   0.1400
  -6.500  -0.0667   0.08969   0.08495  -0.0963   0.8610   0.1432
  -6.250  -0.0763   0.08904   0.08436  -0.0908   0.8501   0.1444
  -6.000  -0.0516   0.08617   0.08146  -0.0920   0.8461   0.1487
  -5.750  -0.0639   0.08460   0.07991  -0.0917   0.8357   0.1532
  -5.500  -0.0649   0.08029   0.07551  -0.0973   0.8278   0.1595
  -5.250  -0.0298   0.07741   0.07264  -0.0980   0.8256   0.1641
  -5.000  -0.0501   0.07713   0.07239  -0.0933   0.8125   0.1666
  -4.750  -0.0281   0.07266   0.06777  -0.0997   0.8080   0.1779
  -4.500  -0.0340   0.07209   0.06724  -0.0954   0.7974   0.1804
  -4.250  -0.0145   0.06880   0.06378  -0.0999   0.7910   0.1950
  -4.000   0.0208   0.06576   0.06059  -0.1042   0.7880   0.2130
  -3.750   0.0601   0.06303   0.05793  -0.1050   0.7865   0.2235
  -3.500   0.0689   0.04908   0.04197  -0.1147   0.7726   0.1151
  -3.250   0.1129   0.04574   0.03822  -0.1176   0.7697   0.1097
  -3.000   0.1618   0.04257   0.03454  -0.1210   0.7679   0.1083
  -2.750   0.1600   0.04292   0.03472  -0.1172   0.7545   0.1091
  -2.500   0.2051   0.04090   0.03221  -0.1193   0.7512   0.1120
  -2.250   0.2563   0.03845   0.02939  -0.1222   0.7494   0.1148
  -2.000   0.2595   0.03888   0.02981  -0.1190   0.7365   0.1167
  -1.750   0.3036   0.03730   0.02809  -0.1207   0.7330   0.1239
  -1.500   0.3547   0.03519   0.02592  -0.1234   0.7313   0.1341
  -1.250   0.3720   0.03520   0.02582  -0.1217   0.7222   0.1420
  -1.000   0.4537   0.03179   0.02254  -0.1285   0.7270   0.1732
  -0.750   0.4509   0.03259   0.02349  -0.1241   0.7135   0.1836
  -0.500   0.5014   0.03101   0.02207  -0.1269   0.7116   0.2236
  -0.250   0.5364   0.03015   0.02145  -0.1275   0.7070   0.2745
   0.000   0.5445   0.03032   0.02206  -0.1247   0.6958   0.3545
   0.250   0.5936   0.02756   0.02098  -0.1254   0.6939   1.0000
   0.500   0.6448   0.02661   0.01967  -0.1283   0.6915   1.0000
   0.750   0.6415   0.02786   0.02085  -0.1238   0.6783   1.0000
   1.000   0.6893   0.02696   0.01969  -0.1261   0.6750   1.0000
   1.250   0.7412   0.02598   0.01845  -0.1292   0.6724   1.0000
   1.500   0.7370   0.02724   0.01969  -0.1245   0.6592   1.0000
   1.750   0.7857   0.02634   0.01858  -0.1271   0.6558   1.0000
   2.000   0.7945   0.02711   0.01930  -0.1242   0.6451   1.0000
   2.250   0.8351   0.02650   0.01852  -0.1257   0.6395   1.0000
   2.500   0.8876   0.02551   0.01732  -0.1290   0.6359   1.0000
   2.750   0.8886   0.02651   0.01832  -0.1248   0.6236   1.0000
   3.000   0.9367   0.02572   0.01735  -0.1275   0.6189   1.0000
   3.250   0.9459   0.02648   0.01810  -0.1246   0.6084   1.0000
   3.500   0.9861   0.02603   0.01751  -0.1262   0.6021   1.0000
   3.750   1.0104   0.02627   0.01767  -0.1256   0.5939   1.0000
   4.000   1.0368   0.02635   0.01767  -0.1252   0.5853   1.0000
   4.250   1.0825   0.02587   0.01700  -0.1278   0.5796   1.0000
   4.500   1.0873   0.02676   0.01794  -0.1242   0.5686   1.0000
   4.750   1.1349   0.02629   0.01727  -0.1271   0.5631   1.0000
   5.000   1.1359   0.02744   0.01850  -0.1231   0.5528   1.0000
   5.250   1.1759   0.02722   0.01813  -0.1249   0.5465   1.0000
   5.500   1.1876   0.02806   0.01900  -0.1226   0.5379   1.0000
   5.750   1.2140   0.02830   0.01918  -0.1223   0.5304   1.0000
   6.000   1.2496   0.02836   0.01910  -0.1236   0.5239   1.0000
   6.250   1.2531   0.02936   0.02019  -0.1200   0.5151   1.0000
   6.500   1.2992   0.02898   0.01961  -0.1227   0.5089   1.0000
   6.750   1.2978   0.03025   0.02101  -0.1185   0.5010   1.0000
   7.000   1.3210   0.03063   0.02135  -0.1179   0.4944   1.0000
   7.250   1.3674   0.03045   0.02099  -0.1208   0.4890   1.0000
   7.500   1.3522   0.03217   0.02293  -0.1147   0.4820   1.0000
   7.750   1.3741   0.03266   0.02341  -0.1140   0.4764   1.0000
   8.000   1.4272   0.03235   0.02291  -0.1179   0.4718   1.0000
   8.250   1.4024   0.03437   0.02519  -0.1105   0.4657   1.0000
   8.500   1.4092   0.03546   0.02634  -0.1079   0.4602   1.0000
   8.750   1.4476   0.03550   0.02632  -0.1096   0.4561   1.0000
   9.000   1.4742   0.03610   0.02691  -0.1098   0.4518   1.0000
   9.250   1.4324   0.03930   0.03038  -0.1011   0.4465   1.0000
   9.500   1.4401   0.04053   0.03168  -0.0990   0.4415   1.0000
   9.750   1.5005   0.03925   0.03026  -0.1029   0.4373   1.0000
  10.000   1.4900   0.04139   0.03254  -0.0986   0.4328   1.0000
  10.250   1.2443   0.06402   0.05576  -0.0802   0.4196   1.0000
  10.500   1.4026   0.05083   0.04239  -0.0859   0.4218   1.0000
  10.750   1.5126   0.04531   0.03668  -0.0927   0.4194   1.0000
  11.750   1.5754   0.04838   0.03992  -0.0883   0.4002   1.0000
  12.000   0.9348   0.13192   0.12427  -0.0828   0.3590   1.0000
  12.250   0.9516   0.13286   0.12523  -0.0824   0.3529   1.0000
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