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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 200,000
Max Cl/Cd: 73.37 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe325-il-200000-n5.txt
Download as CSV file: xf-goe325-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3211   0.09442   0.09108  -0.0259   1.0000   0.0202
  -7.750  -0.3213   0.09174   0.08845  -0.0250   1.0000   0.0195
  -7.500  -0.3275   0.08961   0.08638  -0.0235   1.0000   0.0190
  -7.250  -0.3370   0.08772   0.08456  -0.0216   1.0000   0.0187
  -7.000  -0.3422   0.08531   0.08220  -0.0210   1.0000   0.0184
  -6.750  -0.3235   0.08062   0.07751  -0.0276   0.9956   0.0189
  -6.500  -0.2962   0.07477   0.07162  -0.0377   0.9896   0.0201
  -6.250  -0.2665   0.06884   0.06563  -0.0470   0.9847   0.0202
  -6.000  -0.2351   0.06277   0.05947  -0.0559   0.9789   0.0203
  -5.750  -0.1936   0.05482   0.05132  -0.0676   0.9735   0.0211
  -5.500  -0.1713   0.05353   0.05004  -0.0689   0.9686   0.0228
  -5.250  -0.1372   0.05010   0.04649  -0.0741   0.9647   0.0249
  -5.000  -0.1055   0.04513   0.04132  -0.0793   0.9571   0.0253
  -4.750  -0.0660   0.03980   0.03568  -0.0852   0.9518   0.0270
  -4.500  -0.0311   0.03481   0.03027  -0.0882   0.9420   0.0292
  -4.250  -0.0003   0.02978   0.02479  -0.0909   0.9324   0.0307
  -4.000   0.0260   0.02881   0.02377  -0.0916   0.9200   0.0327
  -3.750   0.0540   0.02692   0.02165  -0.0922   0.9076   0.0346
  -3.500   0.0822   0.02427   0.01863  -0.0925   0.8946   0.0353
  -3.250   0.1107   0.02217   0.01618  -0.0927   0.8802   0.0368
  -3.000   0.1395   0.02034   0.01397  -0.0927   0.8633   0.0385
  -2.750   0.1683   0.01861   0.01185  -0.0925   0.8425   0.0389
  -2.500   0.1968   0.01726   0.01013  -0.0922   0.8165   0.0395
  -2.250   0.2246   0.01625   0.00875  -0.0917   0.7852   0.0401
  -2.000   0.2514   0.01567   0.00780  -0.0910   0.7507   0.0411
  -1.750   0.2779   0.01532   0.00712  -0.0904   0.7169   0.0419
  -1.500   0.3043   0.01470   0.00623  -0.0898   0.6840   0.0421
  -1.250   0.3305   0.01413   0.00541  -0.0893   0.6502   0.0424
  -1.000   0.3565   0.01367   0.00472  -0.0889   0.6167   0.0429
  -0.750   0.3826   0.01333   0.00421  -0.0884   0.5885   0.0438
  -0.500   0.4090   0.01312   0.00385  -0.0881   0.5671   0.0450
  -0.250   0.4357   0.01299   0.00360  -0.0879   0.5497   0.0466
   0.000   0.4626   0.01291   0.00341  -0.0877   0.5347   0.0486
   0.250   0.4897   0.01287   0.00326  -0.0875   0.5214   0.0511
   0.500   0.5168   0.01286   0.00314  -0.0874   0.5095   0.0541
   0.750   0.5440   0.01285   0.00310  -0.0873   0.4980   0.0624
   1.000   0.5714   0.01281   0.00306  -0.0872   0.4863   0.0781
   1.250   0.5987   0.01269   0.00306  -0.0872   0.4747   0.1396
   1.750   0.6471   0.01103   0.00318  -0.0856   0.4528   1.0000
   2.000   0.6743   0.01119   0.00324  -0.0855   0.4410   1.0000
   2.250   0.7014   0.01137   0.00331  -0.0853   0.4290   1.0000
   2.500   0.7283   0.01155   0.00339  -0.0852   0.4170   1.0000
   2.750   0.7550   0.01175   0.00350  -0.0850   0.4054   1.0000
   3.000   0.7817   0.01197   0.00362  -0.0848   0.3946   1.0000
   3.250   0.8084   0.01217   0.00377  -0.0847   0.3846   1.0000
   3.500   0.8349   0.01241   0.00395  -0.0845   0.3759   1.0000
   3.750   0.8614   0.01265   0.00413  -0.0843   0.3673   1.0000
   4.000   0.8878   0.01289   0.00434  -0.0841   0.3593   1.0000
   4.250   0.9140   0.01316   0.00458  -0.0839   0.3520   1.0000
   4.500   0.9403   0.01342   0.00482  -0.0837   0.3457   1.0000
   4.750   0.9666   0.01368   0.00509  -0.0835   0.3398   1.0000
   5.000   0.9925   0.01400   0.00537  -0.0832   0.3348   1.0000
   5.250   1.0189   0.01425   0.00570  -0.0831   0.3296   1.0000
   5.500   1.0448   0.01455   0.00602  -0.0828   0.3244   1.0000
   5.750   1.0704   0.01489   0.00635  -0.0825   0.3199   1.0000
   6.000   1.0966   0.01517   0.00674  -0.0824   0.3151   1.0000
   6.250   1.1218   0.01549   0.00707  -0.0820   0.3079   1.0000
   6.500   1.1470   0.01575   0.00740  -0.0817   0.2974   1.0000
   6.750   1.1717   0.01605   0.00773  -0.0813   0.2875   1.0000
   7.000   1.1959   0.01636   0.00808  -0.0809   0.2755   1.0000
   7.250   1.2202   0.01663   0.00840  -0.0804   0.2588   1.0000
   7.500   1.2440   0.01696   0.00875  -0.0799   0.2390   1.0000
   7.750   1.2668   0.01740   0.00916  -0.0793   0.2143   1.0000
   8.000   1.2809   0.01882   0.01003  -0.0778   0.1263   1.0000
   8.500   1.2994   0.02280   0.01332  -0.0734   0.0201   1.0000
   8.750   1.3159   0.02382   0.01449  -0.0719   0.0174   1.0000
   9.000   1.3320   0.02480   0.01564  -0.0704   0.0158   1.0000
   9.250   1.3466   0.02582   0.01684  -0.0687   0.0146   1.0000
   9.500   1.3585   0.02699   0.01819  -0.0667   0.0138   1.0000
   9.750   1.3665   0.02829   0.01966  -0.0642   0.0132   1.0000
  10.000   1.3699   0.02973   0.02129  -0.0611   0.0127   1.0000
  10.250   1.3708   0.03143   0.02315  -0.0582   0.0123   1.0000
  10.500   1.3686   0.03348   0.02534  -0.0554   0.0118   1.0000
  10.750   1.3621   0.03605   0.02806  -0.0528   0.0114   1.0000
  11.000   1.3523   0.03921   0.03137  -0.0508   0.0110   1.0000
  11.250   1.3500   0.04197   0.03427  -0.0497   0.0107   1.0000
  11.500   1.3502   0.04469   0.03713  -0.0491   0.0104   1.0000
  11.750   1.3482   0.04786   0.04045  -0.0489   0.0101   1.0000
  12.000   1.3451   0.05133   0.04405  -0.0489   0.0100   1.0000
  12.250   1.3419   0.05490   0.04775  -0.0490   0.0098   1.0000
  12.500   1.3390   0.05852   0.05149  -0.0493   0.0096   1.0000
  12.750   1.3362   0.06211   0.05520  -0.0495   0.0094   1.0000
  13.000   1.3340   0.06565   0.05887  -0.0496   0.0093   1.0000
  13.250   1.3320   0.06915   0.06247  -0.0497   0.0091   1.0000
  13.500   1.3304   0.07258   0.06605  -0.0498   0.0090   1.0000
  13.750   1.3290   0.07601   0.06960  -0.0499   0.0088   1.0000
  14.000   1.3279   0.07944   0.07315  -0.0500   0.0087   1.0000
  14.250   1.3266   0.08295   0.07678  -0.0502   0.0086   1.0000
  14.500   1.3245   0.08668   0.08064  -0.0507   0.0084   1.0000
  14.750   1.3219   0.09057   0.08464  -0.0514   0.0082   1.0000
  15.000   1.3189   0.09456   0.08875  -0.0524   0.0081   1.0000
  15.250   1.3156   0.09862   0.09292  -0.0534   0.0079   1.0000
  15.500   1.3125   0.10261   0.09700  -0.0543   0.0077   1.0000
  15.750   1.3090   0.10662   0.10109  -0.0548   0.0075   1.0000
  16.000   1.3017   0.11176   0.10639  -0.0567   0.0074   1.0000
  16.250   1.2929   0.11754   0.11238  -0.0597   0.0073   1.0000
  16.500   1.2844   0.12335   0.11839  -0.0627   0.0072   1.0000
  16.750   1.2756   0.12939   0.12462  -0.0659   0.0072   1.0000
  17.000   1.2662   0.13578   0.13120  -0.0694   0.0071   1.0000
  17.250   1.2570   0.14227   0.13786  -0.0731   0.0071   1.0000
  17.500   1.2475   0.14907   0.14483  -0.0772   0.0071   1.0000
  17.750   1.2375   0.15622   0.15215  -0.0816   0.0071   1.0000
  18.000   1.2274   0.16363   0.15972  -0.0864   0.0071   1.0000
  18.250   1.2173   0.17142   0.16766  -0.0914   0.0072   1.0000
  18.500   1.2072   0.17957   0.17594  -0.0968   0.0072   1.0000
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