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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.65 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe373-il-1000000-n5.txt
Download as CSV file: xf-goe373-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3439   0.11060   0.10895  -0.0178   1.0000   0.0055
  -9.750  -0.3427   0.10635   0.10472  -0.0190   1.0000   0.0059
  -9.500  -0.3389   0.10314   0.10152  -0.0199   1.0000   0.0062
  -9.250  -0.3330   0.10069   0.09908  -0.0206   1.0000   0.0063
  -9.000  -0.3277   0.09821   0.09662  -0.0211   1.0000   0.0064
  -8.750  -0.3212   0.09621   0.09463  -0.0215   1.0000   0.0066
  -8.500  -0.3175   0.09375   0.09219  -0.0218   1.0000   0.0068
  -8.250  -0.3082   0.09074   0.08919  -0.0238   0.9991   0.0071
  -8.000  -0.2984   0.08720   0.08565  -0.0266   0.9904   0.0075
  -7.750  -0.2900   0.08188   0.08034  -0.0317   0.9776   0.0082
  -7.500  -0.2643   0.07858   0.07703  -0.0376   0.9660   0.0084
  -7.250  -0.2207   0.07411   0.07251  -0.0485   0.9516   0.0087
  -7.000  -0.1705   0.06856   0.06682  -0.0621   0.9164   0.0095
  -6.750  -0.1561   0.06356   0.06155  -0.0680   0.8563   0.0105
  -6.500  -0.1424   0.06208   0.05991  -0.0689   0.8210   0.0107
  -6.000  -0.1109   0.05730   0.05492  -0.0731   0.7790   0.0112
  -5.750  -0.0922   0.05461   0.05214  -0.0757   0.7630   0.0116
  -5.500  -0.0678   0.04872   0.04610  -0.0821   0.7510   0.0131
  -5.250  -0.0472   0.04677   0.04406  -0.0836   0.7367   0.0132
  -5.000  -0.0249   0.04476   0.04195  -0.0852   0.7213   0.0134
  -4.750  -0.0015   0.04268   0.03975  -0.0870   0.7057   0.0137
  -4.500   0.0236   0.04022   0.03717  -0.0890   0.6915   0.0140
  -4.250   0.0499   0.03764   0.03447  -0.0909   0.6791   0.0146
  -4.000   0.0826   0.03322   0.02981  -0.0940   0.6681   0.0161
  -3.750   0.1064   0.03176   0.02824  -0.0946   0.6527   0.0163
  -3.500   0.1310   0.03047   0.02683  -0.0952   0.6342   0.0168
  -3.250   0.1573   0.02856   0.02472  -0.0959   0.6123   0.0171
  -3.000   0.1844   0.02646   0.02241  -0.0965   0.5897   0.0173
  -2.750   0.2116   0.02472   0.02045  -0.0968   0.5706   0.0182
  -2.500   0.2392   0.02265   0.01816  -0.0970   0.5559   0.0183
  -2.250   0.2710   0.02050   0.01563  -0.0965   0.5444   0.0192
  -2.000   0.2977   0.01910   0.01401  -0.0964   0.5338   0.0192
  -1.750   0.3227   0.01720   0.01194  -0.0966   0.5241   0.0195
  -1.500   0.3484   0.01660   0.01128  -0.0967   0.5149   0.0199
  -1.250   0.3745   0.01602   0.01059  -0.0966   0.5059   0.0204
  -1.000   0.4015   0.01515   0.00958  -0.0964   0.4975   0.0208
  -0.750   0.4293   0.01360   0.00772  -0.0958   0.4883   0.0200
  -0.500   0.4560   0.01300   0.00698  -0.0956   0.4766   0.0203
  -0.250   0.4829   0.01245   0.00628  -0.0953   0.4642   0.0207
   0.000   0.5099   0.01193   0.00563  -0.0950   0.4537   0.0211
   0.250   0.5368   0.01151   0.00508  -0.0947   0.4438   0.0214
   0.500   0.5638   0.01112   0.00458  -0.0944   0.4327   0.0215
   0.750   0.5906   0.01079   0.00414  -0.0941   0.4192   0.0215
   1.000   0.6172   0.01062   0.00384  -0.0938   0.4023   0.0220
   1.250   0.6434   0.01040   0.00350  -0.0934   0.3841   0.0219
   1.500   0.6696   0.01019   0.00319  -0.0930   0.3671   0.0216
   2.000   0.7224   0.00984   0.00273  -0.0923   0.3456   0.0212
   2.250   0.7488   0.00972   0.00257  -0.0920   0.3378   0.0213
   2.500   0.7753   0.00961   0.00245  -0.0917   0.3306   0.0214
   2.750   0.8016   0.00958   0.00238  -0.0914   0.3231   0.0219
   3.000   0.8282   0.00958   0.00236  -0.0911   0.3154   0.0225
   3.250   0.8545   0.00967   0.00241  -0.0908   0.3057   0.0229
   3.500   0.8802   0.00968   0.00238  -0.0904   0.2913   0.0234
   3.750   0.9060   0.00973   0.00239  -0.0900   0.2757   0.0240
   4.000   0.9309   0.00994   0.00249  -0.0896   0.2489   0.0248
   4.250   0.9546   0.01032   0.00267  -0.0890   0.2052   0.0255
   4.500   0.9771   0.01084   0.00296  -0.0882   0.1613   0.0255
   4.750   1.0017   0.01111   0.00316  -0.0877   0.1435   0.0255
   5.000   1.0263   0.01140   0.00337  -0.0871   0.1250   0.0258
   5.250   1.0489   0.01192   0.00368  -0.0864   0.0895   0.0263
   5.500   1.0680   0.01287   0.00432  -0.0851   0.0314   0.0271
   5.750   1.0915   0.01330   0.00470  -0.0844   0.0142   0.0278
   6.000   1.1162   0.01355   0.00499  -0.0838   0.0118   0.0293
   6.250   1.1410   0.01378   0.00524  -0.0834   0.0111   0.0321
   6.500   1.1655   0.01405   0.00555  -0.0828   0.0101   0.0332
   6.750   1.1895   0.01435   0.00589  -0.0822   0.0091   0.0380
   7.000   1.2149   0.01348   0.00662  -0.0825   0.0081   1.0000
   7.250   1.2387   0.01381   0.00696  -0.0819   0.0078   1.0000
   7.500   1.2620   0.01418   0.00737  -0.0812   0.0073   1.0000
   7.750   1.2849   0.01458   0.00779  -0.0804   0.0069   1.0000
   8.000   1.3075   0.01499   0.00823  -0.0797   0.0064   1.0000
   8.250   1.3297   0.01542   0.00867  -0.0789   0.0059   1.0000
   8.500   1.3500   0.01604   0.00935  -0.0777   0.0055   1.0000
   8.750   1.3714   0.01651   0.00986  -0.0768   0.0053   1.0000
   9.000   1.3919   0.01704   0.01045  -0.0758   0.0051   1.0000
   9.250   1.4119   0.01759   0.01105  -0.0747   0.0049   1.0000
   9.500   1.4310   0.01819   0.01172  -0.0734   0.0046   1.0000
   9.750   1.4495   0.01880   0.01237  -0.0721   0.0044   1.0000
  10.000   1.4674   0.01942   0.01304  -0.0708   0.0042   1.0000
  10.250   1.4845   0.02005   0.01372  -0.0693   0.0041   1.0000
  10.500   1.4998   0.02077   0.01450  -0.0676   0.0039   1.0000
  10.750   1.5125   0.02155   0.01535  -0.0655   0.0038   1.0000
  11.000   1.5163   0.02264   0.01653  -0.0620   0.0036   1.0000
  11.250   1.5242   0.02349   0.01746  -0.0592   0.0035   1.0000
  11.500   1.5317   0.02441   0.01846  -0.0566   0.0034   1.0000
  11.750   1.5369   0.02552   0.01966  -0.0539   0.0034   1.0000
  12.000   1.5434   0.02663   0.02084  -0.0517   0.0033   1.0000
  12.250   1.5469   0.02802   0.02234  -0.0494   0.0032   1.0000
  12.500   1.5474   0.02976   0.02419  -0.0473   0.0031   1.0000
  12.750   1.5485   0.03163   0.02615  -0.0456   0.0031   1.0000
  13.000   1.5484   0.03377   0.02840  -0.0442   0.0030   1.0000
  13.250   1.5483   0.03610   0.03083  -0.0432   0.0029   1.0000
  13.500   1.5457   0.03886   0.03370  -0.0425   0.0029   1.0000
  13.750   1.5428   0.04184   0.03679  -0.0421   0.0028   1.0000
  14.000   1.5383   0.04517   0.04024  -0.0420   0.0028   1.0000
  14.250   1.5317   0.04897   0.04416  -0.0424   0.0028   1.0000
  14.500   1.5242   0.05311   0.04842  -0.0431   0.0027   1.0000
  14.750   1.5212   0.05681   0.05222  -0.0439   0.0027   1.0000
  15.000   1.5146   0.06116   0.05669  -0.0451   0.0026   1.0000
  15.250   1.5045   0.06617   0.06181  -0.0466   0.0026   1.0000
  15.500   1.4995   0.07056   0.06631  -0.0481   0.0026   1.0000
  15.750   1.4876   0.07616   0.07202  -0.0500   0.0026   1.0000
  16.000   1.4764   0.08181   0.07779  -0.0522   0.0026   1.0000
  16.250   1.4675   0.08726   0.08334  -0.0544   0.0025   1.0000
  16.500   1.4573   0.09309   0.08929  -0.0568   0.0025   1.0000
  16.750   1.4464   0.09914   0.09545  -0.0595   0.0025   1.0000
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