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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 50,000
Max Cl/Cd: 33.95 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe167-il-50000-n5.txt
Download as CSV file: xf-goe167-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3458   0.10133   0.09505  -0.0250   1.0000   0.1063
  -7.750  -0.3532   0.09963   0.09349  -0.0307   1.0000   0.1087
  -7.500  -0.3493   0.09591   0.08986  -0.0335   1.0000   0.1099
  -7.250  -0.3361   0.09163   0.08561  -0.0299   1.0000   0.1136
  -7.000  -0.3315   0.08873   0.08280  -0.0317   1.0000   0.1194
  -6.750  -0.3344   0.08672   0.08084  -0.0405   1.0000   0.1237
  -6.500  -0.3252   0.08269   0.07693  -0.0339   1.0000   0.1292
  -6.250  -0.3276   0.08109   0.07536  -0.0394   1.0000   0.1375
  -5.750  -0.2791   0.07186   0.06608  -0.0480   0.9748   0.1550
  -5.500  -0.2474   0.06751   0.06161  -0.0543   0.9557   0.1700
  -5.250  -0.2198   0.06356   0.05763  -0.0569   0.9370   0.1881
  -4.750  -0.1217   0.05100   0.04379  -0.0761   0.8968   0.0932
  -4.500  -0.0815   0.04659   0.03865  -0.0807   0.8781   0.0809
  -4.250  -0.0500   0.04340   0.03516  -0.0828   0.8603   0.0799
  -4.000  -0.0177   0.04084   0.03205  -0.0846   0.8418   0.0808
  -3.750   0.0118   0.03840   0.02923  -0.0856   0.8248   0.0801
  -3.500   0.0409   0.03621   0.02665  -0.0863   0.8089   0.0788
  -3.250   0.0701   0.03433   0.02433  -0.0867   0.7941   0.0778
  -3.000   0.0993   0.03269   0.02225  -0.0870   0.7805   0.0771
  -2.750   0.1284   0.03125   0.02038  -0.0870   0.7682   0.0768
  -2.500   0.1572   0.03005   0.01877  -0.0870   0.7564   0.0772
  -2.250   0.1862   0.02915   0.01746  -0.0870   0.7449   0.0799
  -2.000   0.2150   0.02834   0.01628  -0.0869   0.7349   0.0818
  -1.750   0.2429   0.02739   0.01511  -0.0867   0.7260   0.0826
  -1.500   0.2705   0.02665   0.01421  -0.0865   0.7166   0.0835
  -1.000   0.3260   0.02554   0.01277  -0.0859   0.7008   0.0867
  -0.750   0.3538   0.02512   0.01216  -0.0855   0.6945   0.0892
  -0.500   0.3814   0.02486   0.01178  -0.0855   0.6868   0.0923
  -0.250   0.4091   0.02459   0.01137  -0.0854   0.6808   0.0980
   0.000   0.4368   0.02446   0.01116  -0.0856   0.6742   0.1091
   0.500   0.4940   0.02379   0.01070  -0.0862   0.6634   0.1636
   1.000   0.5449   0.02220   0.01077  -0.0851   0.6522   1.0000
   1.250   0.5726   0.02259   0.01092  -0.0852   0.6475   1.0000
   1.500   0.5996   0.02309   0.01131  -0.0855   0.6417   1.0000
   1.750   0.6270   0.02353   0.01159  -0.0856   0.6371   1.0000
   2.000   0.6545   0.02395   0.01188  -0.0857   0.6331   1.0000
   2.250   0.6806   0.02458   0.01250  -0.0860   0.6274   1.0000
   2.500   0.7074   0.02508   0.01295  -0.0861   0.6227   1.0000
   2.750   0.7348   0.02552   0.01331  -0.0861   0.6191   1.0000
   3.000   0.7598   0.02630   0.01415  -0.0864   0.6137   1.0000
   3.250   0.7856   0.02692   0.01479  -0.0865   0.6087   1.0000
   3.500   0.8127   0.02736   0.01520  -0.0864   0.6046   1.0000
   3.750   0.8364   0.02817   0.01612  -0.0864   0.5980   1.0000
   4.000   0.8621   0.02864   0.01660  -0.0862   0.5916   1.0000
   4.250   0.8866   0.02919   0.01720  -0.0858   0.5841   1.0000
   4.500   0.9121   0.02950   0.01756  -0.0852   0.5758   1.0000
   4.750   0.9353   0.03003   0.01818  -0.0847   0.5662   1.0000
   5.000   0.9625   0.03016   0.01832  -0.0841   0.5590   1.0000
   5.250   0.9837   0.03102   0.01938  -0.0837   0.5502   1.0000
   5.500   1.0100   0.03140   0.01984  -0.0833   0.5444   1.0000
   5.750   1.0309   0.03234   0.02099  -0.0829   0.5365   1.0000
   6.000   1.0560   0.03281   0.02161  -0.0824   0.5300   1.0000
   6.250   1.0767   0.03371   0.02272  -0.0819   0.5217   1.0000
   6.500   1.1025   0.03395   0.02309  -0.0812   0.5139   1.0000
   6.750   1.1215   0.03472   0.02407  -0.0803   0.5027   1.0000
   7.000   1.1439   0.03499   0.02455  -0.0792   0.4915   1.0000
   7.250   1.1698   0.03481   0.02449  -0.0782   0.4806   1.0000
   7.500   1.1905   0.03508   0.02498  -0.0770   0.4680   1.0000
   7.750   1.2079   0.03563   0.02578  -0.0756   0.4547   1.0000
   8.000   1.2253   0.03609   0.02648  -0.0742   0.4410   1.0000
   8.250   1.2415   0.03668   0.02738  -0.0727   0.4278   1.0000
   8.500   1.2571   0.03742   0.02839  -0.0713   0.4158   1.0000
   8.750   1.2719   0.03808   0.02933  -0.0697   0.4028   1.0000
   9.000   1.2815   0.03886   0.03037  -0.0676   0.3856   1.0000
   9.250   1.2930   0.03908   0.03074  -0.0652   0.3643   1.0000
   9.500   1.2930   0.04038   0.03221  -0.0625   0.3385   1.0000
   9.750   1.2928   0.04142   0.03329  -0.0595   0.3091   1.0000
  10.000   1.2918   0.04276   0.03439  -0.0567   0.2723   1.0000
  10.250   1.2839   0.04534   0.03667  -0.0546   0.2393   1.0000
  10.500   1.2734   0.04889   0.04011  -0.0536   0.2121   1.0000
  10.750   1.2633   0.05287   0.04412  -0.0532   0.1830   1.0000
  11.000   1.2506   0.05730   0.04844  -0.0531   0.1396   1.0000
  11.250   1.2335   0.06229   0.05306  -0.0532   0.1143   1.0000
  11.500   1.2179   0.06727   0.05777  -0.0533   0.0997   1.0000
  11.750   1.2046   0.07206   0.06242  -0.0535   0.0892   1.0000
  12.000   1.1935   0.07667   0.06700  -0.0536   0.0811   1.0000
  12.250   1.1822   0.08132   0.07162  -0.0538   0.0745   1.0000
  12.500   1.1747   0.08557   0.07593  -0.0538   0.0680   1.0000
  12.750   1.1682   0.08969   0.08010  -0.0538   0.0625   1.0000
  13.000   1.1638   0.09346   0.08386  -0.0536   0.0580   1.0000
  13.250   1.1652   0.09665   0.08724  -0.0532   0.0529   1.0000
  13.500   1.1658   0.09989   0.09054  -0.0531   0.0489   1.0000
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