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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 500,000
Max Cl/Cd: 109.96 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe397-il-500000.txt
Download as CSV file: xf-goe397-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 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  -0.3907   0.08829   0.08607  -0.0184   1.0000   0.0155
  -7.500  -0.3888   0.08591   0.08372  -0.0186   1.0000   0.0160
  -7.250  -0.3869   0.08344   0.08128  -0.0192   1.0000   0.0167
  -7.000  -0.3809   0.08049   0.07836  -0.0210   1.0000   0.0172
  -6.750  -0.3735   0.07736   0.07524  -0.0233   1.0000   0.0177
  -6.500  -0.3611   0.07421   0.07210  -0.0274   1.0000   0.0189
  -6.250  -0.3448   0.07092   0.06880  -0.0326   1.0000   0.0193
  -6.000  -0.3318   0.06758   0.06544  -0.0351   1.0000   0.0195
  -5.750  -0.3185   0.06420   0.06203  -0.0371   0.9996   0.0195
  -5.500  -0.2793   0.05850   0.05624  -0.0453   0.9953   0.0196
  -5.250  -0.2462   0.04991   0.04751  -0.0539   0.9889   0.0201
  -5.000  -0.2186   0.04654   0.04410  -0.0575   0.9842   0.0209
  -4.750  -0.1888   0.04427   0.04178  -0.0606   0.9777   0.0227
  -4.500  -0.1434   0.04049   0.03780  -0.0663   0.9718   0.0266
  -4.250  -0.1008   0.03692   0.03396  -0.0703   0.9632   0.0274
  -4.000  -0.0638   0.03262   0.02937  -0.0737   0.9541   0.0276
  -3.750  -0.0378   0.02599   0.02244  -0.0768   0.9401   0.0294
  -3.500  -0.0105   0.02472   0.02107  -0.0777   0.9249   0.0314
  -3.250   0.0172   0.02293   0.01904  -0.0779   0.9086   0.0354
  -3.000   0.0482   0.02287   0.01860  -0.0770   0.8930   0.0387
  -1.500   0.0939   0.01990   0.01595  -0.0665   0.7930   0.0443
  -1.250   0.2220   0.01131   0.00515  -0.0726   0.7936   0.0453
  -1.000   0.2484   0.01044   0.00409  -0.0719   0.7812   0.0435
  -0.750   0.2746   0.00992   0.00346  -0.0713   0.7695   0.0431
  -0.500   0.3008   0.00951   0.00296  -0.0708   0.7589   0.0429
  -0.250   0.3271   0.00920   0.00262  -0.0704   0.7482   0.0439
   0.000   0.3534   0.00892   0.00229  -0.0699   0.7383   0.0442
   0.250   0.3796   0.00868   0.00200  -0.0694   0.7292   0.0439
   0.500   0.4061   0.00847   0.00178  -0.0690   0.7198   0.0442
   0.750   0.4326   0.00832   0.00160  -0.0686   0.7112   0.0455
   1.000   0.4591   0.00823   0.00147  -0.0682   0.7028   0.0479
   1.250   0.4859   0.00816   0.00138  -0.0679   0.6942   0.0511
   1.500   0.5127   0.00813   0.00133  -0.0676   0.6869   0.0578
   1.750   0.5367   0.00747   0.00147  -0.0671   0.6790   0.3785
   2.000   0.5890   0.00613   0.00152  -0.0729   0.6690   1.0000
   2.250   0.6144   0.00624   0.00155  -0.0722   0.6542   1.0000
   2.500   0.6401   0.00635   0.00161  -0.0717   0.6430   1.0000
   2.750   0.6657   0.00647   0.00168  -0.0711   0.6305   1.0000
   3.000   0.6909   0.00658   0.00177  -0.0705   0.6113   1.0000
   3.250   0.7158   0.00672   0.00184  -0.0698   0.5903   1.0000
   3.500   0.7413   0.00683   0.00194  -0.0692   0.5696   1.0000
   3.750   0.7664   0.00697   0.00204  -0.0686   0.5433   1.0000
   4.250   0.8097   0.00791   0.00242  -0.0662   0.4033   1.0000
   4.500   0.8297   0.00870   0.00279  -0.0650   0.3163   1.0000
   4.750   0.8428   0.01041   0.00355  -0.0630   0.1213   1.0000
   5.000   0.8636   0.01123   0.00408  -0.0620   0.0703   1.0000
   5.250   0.8868   0.01172   0.00455  -0.0612   0.0561   1.0000
   5.500   0.9104   0.01215   0.00500  -0.0604   0.0463   1.0000
   5.750   0.9331   0.01270   0.00554  -0.0595   0.0347   1.0000
   6.000   0.9550   0.01336   0.00621  -0.0585   0.0268   1.0000
   6.250   0.9774   0.01393   0.00679  -0.0575   0.0226   1.0000
   6.500   0.9953   0.01509   0.00808  -0.0558   0.0200   1.0000
   6.750   1.0164   0.01582   0.00889  -0.0546   0.0187   1.0000
   7.000   1.0373   0.01655   0.00969  -0.0534   0.0171   1.0000
   7.250   1.0586   0.01719   0.01035  -0.0525   0.0154   1.0000
   7.500   1.0740   0.01883   0.01210  -0.0505   0.0143   1.0000
   7.750   1.0896   0.02111   0.01455  -0.0485   0.0136   1.0000
   8.000   1.1103   0.02232   0.01593  -0.0474   0.0132   1.0000
   8.250   1.1303   0.02395   0.01774  -0.0461   0.0127   1.0000
   8.500   1.1492   0.02620   0.02023  -0.0446   0.0123   1.0000
   8.750   1.1660   0.02898   0.02332  -0.0430   0.0121   1.0000
   9.000   1.1822   0.03099   0.02558  -0.0414   0.0115   1.0000
   9.250   1.1966   0.03296   0.02777  -0.0398   0.0110   1.0000
   9.500   1.1963   0.03926   0.03470  -0.0362   0.0115   1.0000
   9.750   1.1900   0.04506   0.04097  -0.0327   0.0121   1.0000
  10.000   1.1794   0.05016   0.04643  -0.0293   0.0126   1.0000
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