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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 500,000
Max Cl/Cd: 98.8 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe316-il-500000-n5.txt
Download as CSV file: xf-goe316-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4107   0.09259   0.09048  -0.0059   0.9439   0.0114
  -8.250  -0.4119   0.08912   0.08685  -0.0067   0.8673   0.0120
  -8.000  -0.4185   0.08320   0.08078  -0.0109   0.8293   0.0126
  -7.750  -0.4107   0.07880   0.07626  -0.0157   0.8062   0.0129
  -7.500  -0.3975   0.07590   0.07327  -0.0189   0.7877   0.0130
  -7.250  -0.3828   0.07263   0.06991  -0.0226   0.7731   0.0133
  -7.000  -0.3667   0.06890   0.06608  -0.0269   0.7610   0.0137
  -6.750  -0.3490   0.06469   0.06178  -0.0315   0.7506   0.0142
  -6.500  -0.3285   0.05448   0.05133  -0.0417   0.7440   0.0161
  -6.250  -0.3073   0.05230   0.04905  -0.0434   0.7344   0.0163
  -6.000  -0.2850   0.05004   0.04669  -0.0451   0.7250   0.0167
  -5.750  -0.2617   0.04721   0.04371  -0.0471   0.7160   0.0172
  -5.500  -0.2369   0.04374   0.04007  -0.0493   0.7073   0.0183
  -5.250  -0.2092   0.03584   0.03168  -0.0526   0.7008   0.0202
  -5.000  -0.1844   0.03447   0.03019  -0.0532   0.6899   0.0205
  -4.750  -0.1592   0.03322   0.02881  -0.0536   0.6778   0.0210
  -4.500  -0.1332   0.03149   0.02690  -0.0541   0.6656   0.0219
  -4.250  -0.1059   0.02859   0.02370  -0.0546   0.6535   0.0229
  -4.000  -0.0760   0.02374   0.01826  -0.0546   0.6430   0.0247
  -3.750  -0.0500   0.02167   0.01592  -0.0550   0.6306   0.0253
  -3.500  -0.0229   0.02051   0.01456  -0.0552   0.6162   0.0257
  -3.250   0.0046   0.01948   0.01332  -0.0553   0.6000   0.0260
  -3.000   0.0323   0.01837   0.01198  -0.0553   0.5830   0.0264
  -2.750   0.0603   0.01732   0.01069  -0.0554   0.5659   0.0269
  -2.500   0.0883   0.01649   0.00963  -0.0554   0.5492   0.0277
  -2.250   0.1166   0.01540   0.00827  -0.0553   0.5332   0.0282
  -2.000   0.1449   0.01452   0.00714  -0.0553   0.5170   0.0288
  -1.750   0.1731   0.01384   0.00626  -0.0553   0.5005   0.0293
  -1.500   0.2012   0.01330   0.00555  -0.0553   0.4829   0.0297
  -1.250   0.2294   0.01288   0.00497  -0.0553   0.4638   0.0301
  -1.000   0.2574   0.01257   0.00451  -0.0553   0.4425   0.0304
  -0.750   0.2855   0.01247   0.00427  -0.0553   0.4182   0.0308
  -0.500   0.3130   0.01198   0.00364  -0.0553   0.3945   0.0316
  -0.250   0.3409   0.01174   0.00331  -0.0553   0.3765   0.0321
   0.000   0.3688   0.01160   0.00310  -0.0554   0.3635   0.0327
   0.250   0.3970   0.01148   0.00293  -0.0555   0.3542   0.0334
   0.500   0.4251   0.01140   0.00280  -0.0555   0.3470   0.0342
   0.750   0.4533   0.01131   0.00269  -0.0556   0.3413   0.0350
   1.000   0.4815   0.01126   0.00260  -0.0557   0.3362   0.0359
   1.250   0.5098   0.01123   0.00254  -0.0558   0.3321   0.0368
   1.500   0.5381   0.01120   0.00251  -0.0559   0.3288   0.0380
   1.750   0.5664   0.01118   0.00249  -0.0560   0.3253   0.0394
   2.000   0.5946   0.01116   0.00246  -0.0561   0.3220   0.0416
   2.250   0.6227   0.01120   0.00249  -0.0561   0.3189   0.0441
   2.500   0.6508   0.01125   0.00253  -0.0562   0.3164   0.0473
   2.750   0.6791   0.01127   0.00257  -0.0563   0.3145   0.0533
   3.000   0.7073   0.01129   0.00265  -0.0564   0.3125   0.0696
   3.500   0.7589   0.00952   0.00295  -0.0560   0.3087   1.0000
   3.750   0.7867   0.00967   0.00308  -0.0560   0.3068   1.0000
   4.000   0.8145   0.00984   0.00321  -0.0561   0.3046   1.0000
   4.250   0.8419   0.01005   0.00337  -0.0561   0.3012   1.0000
   4.500   0.8699   0.01014   0.00349  -0.0561   0.2980   1.0000
   4.750   0.8977   0.01027   0.00362  -0.0562   0.2941   1.0000
   5.000   0.9253   0.01043   0.00376  -0.0562   0.2897   1.0000
   5.250   0.9525   0.01064   0.00395  -0.0562   0.2857   1.0000
   5.500   0.9803   0.01076   0.00411  -0.0563   0.2832   1.0000
   5.750   1.0079   0.01090   0.00428  -0.0563   0.2805   1.0000
   6.000   1.0353   0.01105   0.00447  -0.0564   0.2772   1.0000
   6.250   1.0625   0.01123   0.00466  -0.0564   0.2738   1.0000
   6.500   1.0895   0.01142   0.00486  -0.0564   0.2698   1.0000
   6.750   1.1170   0.01155   0.00506  -0.0564   0.2655   1.0000
   7.000   1.1440   0.01172   0.00526  -0.0564   0.2597   1.0000
   7.250   1.1710   0.01190   0.00546  -0.0564   0.2513   1.0000
   7.500   1.1975   0.01212   0.00566  -0.0564   0.2369   1.0000
   7.750   1.2225   0.01255   0.00593  -0.0563   0.2009   1.0000
   8.000   1.2422   0.01369   0.00672  -0.0557   0.1464   1.0000
   8.250   1.2644   0.01447   0.00738  -0.0552   0.1209   1.0000
   8.500   1.2858   0.01532   0.00809  -0.0547   0.0927   1.0000
   8.750   1.3047   0.01642   0.00900  -0.0539   0.0606   1.0000
   9.000   1.3274   0.01700   0.00960  -0.0535   0.0536   1.0000
   9.250   1.3491   0.01766   0.01027  -0.0529   0.0474   1.0000
   9.500   1.3718   0.01817   0.01083  -0.0525   0.0427   1.0000
   9.750   1.3924   0.01887   0.01154  -0.0518   0.0353   1.0000
  10.000   1.4101   0.01981   0.01240  -0.0509   0.0219   1.0000
  10.250   1.4274   0.02073   0.01331  -0.0498   0.0167   1.0000
  10.500   1.4440   0.02165   0.01427  -0.0487   0.0144   1.0000
  10.750   1.4608   0.02247   0.01518  -0.0476   0.0131   1.0000
  11.000   1.4758   0.02337   0.01617  -0.0463   0.0121   1.0000
  11.250   1.4876   0.02441   0.01729  -0.0447   0.0112   1.0000
  11.500   1.4929   0.02565   0.01862  -0.0422   0.0104   1.0000
  11.750   1.5003   0.02686   0.01993  -0.0404   0.0100   1.0000
  12.000   1.5067   0.02829   0.02147  -0.0389   0.0097   1.0000
  12.250   1.5118   0.03002   0.02331  -0.0378   0.0093   1.0000
  12.500   1.5157   0.03206   0.02547  -0.0371   0.0090   1.0000
  12.750   1.5183   0.03444   0.02796  -0.0368   0.0087   1.0000
  13.000   1.5191   0.03716   0.03080  -0.0368   0.0084   1.0000
  13.250   1.5175   0.04029   0.03404  -0.0370   0.0082   1.0000
  13.500   1.5131   0.04386   0.03773  -0.0374   0.0079   1.0000
  13.750   1.5051   0.04803   0.04202  -0.0382   0.0078   1.0000
  14.000   1.4946   0.05268   0.04680  -0.0392   0.0076   1.0000
  14.250   1.4880   0.05690   0.05115  -0.0402   0.0075   1.0000
  14.500   1.4797   0.06140   0.05578  -0.0413   0.0074   1.0000
  14.750   1.4706   0.06608   0.06058  -0.0425   0.0073   1.0000
  15.000   1.4598   0.07103   0.06565  -0.0438   0.0072   1.0000
  15.250   1.4494   0.07608   0.07083  -0.0452   0.0071   1.0000
  15.500   1.4392   0.08122   0.07607  -0.0467   0.0070   1.0000
  15.750   1.4291   0.08637   0.08133  -0.0483   0.0068   1.0000
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