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GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 746 AIRFOIL (goe746-il)
Reynolds number: 50,000
Max Cl/Cd: 20.78 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe746-il-50000-n5.txt
Download as CSV file: xf-goe746-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 746 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3597   0.11029   0.10451   0.0045   0.7631   0.0886
  -8.250  -0.3648   0.10910   0.10335   0.0006   0.7554   0.0911
  -8.000  -0.3716   0.10811   0.10242  -0.0045   0.7469   0.0918
  -7.750  -0.3467   0.10103   0.09527  -0.0007   0.7398   0.0957
  -7.500  -0.3384   0.09785   0.09210  -0.0021   0.7317   0.0993
  -7.250  -0.3376   0.09559   0.08982  -0.0043   0.7256   0.1033
  -7.000  -0.3392   0.09491   0.08911  -0.0122   0.7186   0.1064
  -6.750  -0.3241   0.08924   0.08347  -0.0093   0.7124   0.1095
  -6.500  -0.3126   0.08615   0.08034  -0.0101   0.7061   0.1164
  -6.250  -0.3059   0.08385   0.07798  -0.0155   0.7000   0.1225
  -6.000  -0.2926   0.08006   0.07414  -0.0135   0.6949   0.1300
  -5.750  -0.2806   0.07728   0.07129  -0.0178   0.6886   0.1384
  -5.500  -0.2662   0.07396   0.06793  -0.0174   0.6830   0.1454
  -5.250  -0.2529   0.07108   0.06493  -0.0197   0.6783   0.1545
  -4.750  -0.2214   0.06570   0.05936  -0.0224   0.6671   0.1837
  -4.500  -0.2071   0.06273   0.05636  -0.0215   0.6626   0.2019
  -4.250  -0.1910   0.06055   0.05408  -0.0224   0.6567   0.2304
  -3.750  -0.1162   0.05069   0.04288  -0.0301   0.6490   0.0875
  -3.500  -0.0915   0.04804   0.03998  -0.0311   0.6429   0.0850
  -3.250  -0.0676   0.04564   0.03721  -0.0312   0.6382   0.0838
  -3.000  -0.0397   0.04336   0.03409  -0.0306   0.6346   0.0777
  -2.750  -0.0153   0.04128   0.03183  -0.0309   0.6292   0.0765
  -2.500   0.0098   0.03947   0.02970  -0.0307   0.6242   0.0754
  -2.250   0.0349   0.03783   0.02766  -0.0300   0.6203   0.0747
  -2.000   0.0617   0.03662   0.02600  -0.0298   0.6157   0.0762
  -1.750   0.0892   0.03564   0.02462  -0.0298   0.6103   0.0775
  -1.500   0.1161   0.03451   0.02314  -0.0294   0.6062   0.0775
  -1.250   0.1436   0.03350   0.02180  -0.0289   0.6026   0.0774
  -1.000   0.1728   0.03291   0.02100  -0.0296   0.5966   0.0776
  -0.750   0.2024   0.03225   0.02010  -0.0298   0.5922   0.0781
  -0.500   0.2372   0.03140   0.01899  -0.0305   0.5887   0.0792
  -0.250   0.2699   0.03117   0.01871  -0.0320   0.5828   0.0824
   0.000   0.2995   0.03096   0.01838  -0.0325   0.5780   0.0874
   0.250   0.3272   0.03069   0.01791  -0.0321   0.5744   0.0912
   0.500   0.3535   0.03069   0.01788  -0.0322   0.5695   0.0942
   0.750   0.3786   0.03085   0.01803  -0.0324   0.5641   0.0988
   1.000   0.4033   0.03081   0.01787  -0.0316   0.5602   0.1055
   1.250   0.4274   0.03071   0.01777  -0.0307   0.5569   0.1186
   1.500   0.4481   0.03099   0.01867  -0.0312   0.5500   0.2074
   1.750   0.5405   0.02950   0.01841  -0.0430   0.5450   1.0000
   2.000   0.5635   0.02986   0.01853  -0.0420   0.5415   1.0000
   2.250   0.5850   0.03111   0.01975  -0.0427   0.5340   1.0000
   2.500   0.6074   0.03152   0.02001  -0.0417   0.5298   1.0000
   2.750   0.6303   0.03175   0.02007  -0.0404   0.5266   1.0000
   3.000   0.6488   0.03333   0.02170  -0.0411   0.5180   1.0000
   3.250   0.6711   0.03366   0.02194  -0.0400   0.5139   1.0000
   3.500   0.6903   0.03468   0.02295  -0.0396   0.5077   1.0000
   3.750   0.7093   0.03563   0.02389  -0.0392   0.5010   1.0000
   4.000   0.7325   0.03573   0.02392  -0.0377   0.4974   1.0000
   4.250   0.7458   0.03753   0.02579  -0.0379   0.4883   1.0000
   4.500   0.7679   0.03778   0.02601  -0.0367   0.4836   1.0000
   5.000   0.8005   0.03993   0.02825  -0.0353   0.4696   1.0000
   5.250   0.8257   0.03974   0.02802  -0.0337   0.4664   1.0000
   5.500   0.8299   0.04227   0.03067  -0.0338   0.4554   1.0000
   5.750   0.8551   0.04208   0.03048  -0.0323   0.4519   1.0000
   6.000   0.8553   0.04491   0.03344  -0.0322   0.4408   1.0000
   6.250   0.8810   0.04463   0.03319  -0.0307   0.4373   1.0000
   6.500   0.8767   0.04782   0.03647  -0.0306   0.4257   1.0000
   6.750   0.9026   0.04751   0.03621  -0.0290   0.4224   1.0000
   7.000   0.8928   0.05137   0.04015  -0.0293   0.4101   1.0000
   7.250   0.9202   0.05079   0.03966  -0.0276   0.4073   1.0000
   7.500   0.9032   0.05523   0.04413  -0.0278   0.3947   1.0000
   7.750   0.9288   0.05495   0.04394  -0.0263   0.3916   1.0000
   8.000   0.9096   0.05928   0.04828  -0.0259   0.3797   1.0000
   8.500   0.9150   0.06393   0.05305  -0.0247   0.3652   1.0000
   9.000   0.9195   0.06896   0.05824  -0.0240   0.3509   1.0000
   9.500   0.9194   0.07498   0.06440  -0.0239   0.3372   1.0000
   9.750   0.9419   0.07529   0.06486  -0.0228   0.3345   1.0000
  10.000   0.9177   0.08153   0.07110  -0.0243   0.3242   1.0000
  10.250   0.9373   0.08218   0.07191  -0.0234   0.3209   1.0000
  10.500   0.9184   0.08805   0.07780  -0.0249   0.3126   1.0000
  10.750   0.9271   0.09035   0.08023  -0.0248   0.3084   1.0000
  11.000   0.9472   0.09106   0.08115  -0.0239   0.3057   1.0000
  12.000   0.9271   0.10815   0.09860  -0.0277   0.2825   1.0000
  13.000   0.9844   0.10869   0.09991  -0.0238   0.2442   1.0000
  13.500   1.0161   0.10620   0.09787  -0.0211   0.2146   1.0000
  14.000   1.0307   0.10786   0.09989  -0.0211   0.1759   1.0000
  14.250   1.0172   0.11399   0.10612  -0.0235   0.1604   1.0000
  14.500   1.0047   0.12020   0.11244  -0.0261   0.1437   1.0000
  14.750   1.0255   0.11758   0.10890  -0.0241   0.0656   1.0000
  15.000   1.0194   0.12236   0.11357  -0.0257   0.0578   1.0000
  15.250   1.0143   0.12701   0.11813  -0.0274   0.0525   1.0000
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