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GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 437 AIRFOIL (goe437-il)
Reynolds number: 500,000
Max Cl/Cd: 106.84 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe437-il-500000.txt
Download as CSV file: xf-goe437-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 437 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3269   0.09178   0.08969  -0.0267   1.0000   0.0148
  -7.500  -0.3344   0.09010   0.08806  -0.0248   1.0000   0.0149
  -7.250  -0.3441   0.08853   0.08654  -0.0225   1.0000   0.0149
  -7.000  -0.3461   0.08614   0.08419  -0.0225   0.9998   0.0149
  -6.750  -0.3171   0.08088   0.07892  -0.0311   0.9963   0.0150
  -6.500  -0.2878   0.07567   0.07368  -0.0394   0.9926   0.0150
  -6.250  -0.2674   0.06800   0.06601  -0.0478   0.9876   0.0157
  -6.000  -0.2387   0.06401   0.06199  -0.0534   0.9845   0.0162
  -5.750  -0.2079   0.06001   0.05795  -0.0596   0.9804   0.0169
  -5.500  -0.1748   0.05553   0.05342  -0.0668   0.9749   0.0178
  -5.250  -0.1335   0.05023   0.04802  -0.0759   0.9714   0.0199
  -5.000  -0.0803   0.04491   0.04251  -0.0857   0.9683   0.0222
  -4.750  -0.0449   0.03970   0.03710  -0.0909   0.9611   0.0223
  -4.500  -0.0142   0.03212   0.02928  -0.0973   0.9560   0.0242
  -4.250   0.0126   0.03011   0.02716  -0.0986   0.9462   0.0258
  -4.000   0.0502   0.02863   0.02541  -0.0998   0.9371   0.0321
  -3.750   0.0708   0.01516   0.01059  -0.1006   0.9238   0.0182
  -3.500   0.0980   0.01269   0.00760  -0.1000   0.9095   0.0182
  -3.250   0.1255   0.01156   0.00620  -0.0995   0.8926   0.0197
  -3.000   0.1529   0.01073   0.00513  -0.0990   0.8757   0.0212
  -2.750   0.1795   0.00986   0.00404  -0.0985   0.8594   0.0240
  -2.500   0.2059   0.00940   0.00347  -0.0980   0.8427   0.0276
  -2.250   0.2325   0.00913   0.00306  -0.0974   0.8266   0.0317
  -2.000   0.2583   0.00868   0.00252  -0.0968   0.8114   0.0410
  -1.750   0.2844   0.00839   0.00214  -0.0963   0.7968   0.0522
  -1.500   0.3106   0.00822   0.00188  -0.0958   0.7832   0.0636
  -1.250   0.3370   0.00813   0.00178  -0.0954   0.7701   0.0827
  -1.000   0.3635   0.00810   0.00174  -0.0949   0.7567   0.1116
  -0.750   0.3897   0.00804   0.00167  -0.0945   0.7434   0.1307
  -0.500   0.4161   0.00802   0.00159  -0.0941   0.7302   0.1450
  -0.250   0.4424   0.00800   0.00154  -0.0937   0.7167   0.1577
   0.000   0.4686   0.00797   0.00150  -0.0933   0.7019   0.1745
   0.250   0.4945   0.00790   0.00147  -0.0929   0.6856   0.2085
   0.500   0.5139   0.00683   0.00156  -0.0917   0.6684   0.6509
   0.750   0.5620   0.00620   0.00152  -0.0959   0.6465   1.0000
   1.000   0.5869   0.00633   0.00151  -0.0952   0.6229   1.0000
   1.250   0.6116   0.00648   0.00151  -0.0945   0.5979   1.0000
   1.500   0.6363   0.00667   0.00155  -0.0938   0.5758   1.0000
   1.750   0.6611   0.00686   0.00161  -0.0931   0.5574   1.0000
   2.000   0.6863   0.00705   0.00169  -0.0925   0.5426   1.0000
   2.250   0.7117   0.00723   0.00179  -0.0920   0.5297   1.0000
   2.500   0.7372   0.00740   0.00191  -0.0915   0.5177   1.0000
   2.750   0.7627   0.00758   0.00203  -0.0910   0.5060   1.0000
   3.000   0.7882   0.00776   0.00215  -0.0906   0.4947   1.0000
   3.250   0.8137   0.00793   0.00228  -0.0901   0.4836   1.0000
   3.500   0.8395   0.00808   0.00242  -0.0897   0.4720   1.0000
   3.750   0.8652   0.00824   0.00258  -0.0893   0.4600   1.0000
   4.000   0.8907   0.00841   0.00273  -0.0888   0.4475   1.0000
   4.250   0.9156   0.00860   0.00287  -0.0883   0.4297   1.0000
   4.500   0.9402   0.00880   0.00300  -0.0877   0.4056   1.0000
   4.750   0.9646   0.00905   0.00320  -0.0871   0.3865   1.0000
   5.000   0.9884   0.00935   0.00340  -0.0864   0.3600   1.0000
   5.250   1.0114   0.00973   0.00365  -0.0856   0.3298   1.0000
   5.500   1.0344   0.01012   0.00393  -0.0848   0.2967   1.0000
   5.750   1.0457   0.01176   0.00470  -0.0825   0.1453   1.0000
   6.000   1.0546   0.01382   0.00609  -0.0796   0.0234   1.0000
   6.250   1.0770   0.01434   0.00675  -0.0786   0.0204   1.0000
   6.500   1.0984   0.01495   0.00747  -0.0774   0.0182   1.0000
   6.750   1.1179   0.01576   0.00837  -0.0760   0.0164   1.0000
   7.000   1.1293   0.01731   0.01010  -0.0732   0.0143   1.0000
   7.250   1.1474   0.01811   0.01098  -0.0716   0.0137   1.0000
   7.500   1.1641   0.01901   0.01196  -0.0698   0.0132   1.0000
   7.750   1.1789   0.02005   0.01312  -0.0677   0.0126   1.0000
   8.000   1.1918   0.02127   0.01443  -0.0653   0.0121   1.0000
   8.250   1.2040   0.02265   0.01590  -0.0628   0.0117   1.0000
   8.500   1.2168   0.02424   0.01757  -0.0604   0.0117   1.0000
   8.750   1.2321   0.02591   0.01933  -0.0586   0.0115   1.0000
   9.000   1.2486   0.02730   0.02080  -0.0570   0.0109   1.0000
   9.250   1.2634   0.02855   0.02210  -0.0554   0.0101   1.0000
   9.500   1.2825   0.03061   0.02428  -0.0543   0.0100   1.0000
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