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St. CYR 234 (Bartel 17-IC) (stcyr234-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 234 (Bartel 17-IC) (stcyr234-il)
Reynolds number: 50,000
Max Cl/Cd: 27.97 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr234-il-50000.txt
Download as CSV file: xf-stcyr234-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: St. CYR 234 (Bartel 17-IC)                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3389   0.12940   0.12237  -0.0058   1.0000   0.2989
 -11.500  -0.3512   0.12884   0.12186  -0.0042   1.0000   0.3061
 -11.250  -0.4107   0.13260   0.12576  -0.0022   1.0000   0.3100
 -11.000  -0.3651   0.12530   0.11841  -0.0012   1.0000   0.3147
 -10.750  -0.3593   0.12320   0.11634   0.0005   1.0000   0.3209
 -10.500  -0.3841   0.12339   0.11660   0.0024   1.0000   0.3287
 -10.250  -0.4197   0.12342   0.11673   0.0045   1.0000   0.3319
 -10.000  -0.3835   0.11844   0.11172   0.0054   1.0000   0.3369
  -9.750  -0.3840   0.11680   0.11009   0.0072   1.0000   0.3445
  -9.500  -0.4430   0.11870   0.11211   0.0109   1.0000   0.3511
  -9.250  -0.4112   0.11371   0.10712   0.0112   1.0000   0.3560
  -9.000  -0.4035   0.11151   0.10493   0.0128   1.0000   0.3632
  -8.750  -0.4604   0.11259   0.10612   0.0176   1.0000   0.3714
  -8.500  -0.4505   0.10899   0.10254   0.0187   1.0000   0.3756
  -8.250  -0.4329   0.10628   0.09983   0.0198   1.0000   0.3824
  -8.000  -0.4962   0.10685   0.10051   0.0222   1.0000   0.3936
  -7.750  -0.4642   0.10274   0.09640   0.0249   1.0000   0.3982
  -7.500  -0.4671   0.10103   0.09471   0.0270   1.0000   0.4094
  -7.000  -0.4964   0.09758   0.09133   0.0290   1.0000   0.4352
  -6.750  -0.4763   0.09432   0.08812   0.0325   1.0000   0.4405
  -6.500  -0.4866   0.09255   0.08637   0.0337   1.0000   0.4572
  -6.250  -0.4740   0.09019   0.08405   0.0365   1.0000   0.4657
  -6.000  -0.4755   0.08813   0.08202   0.0385   1.0000   0.4816
  -5.750  -0.4059   0.06736   0.05977  -0.0162   1.0000   0.2889
  -5.500  -0.3918   0.06522   0.05768  -0.0153   1.0000   0.2853
  -5.250  -0.3559   0.05888   0.05057  -0.0248   1.0000   0.2686
  -5.000  -0.3359   0.05680   0.04831  -0.0258   1.0000   0.2680
  -4.750  -0.3142   0.05482   0.04603  -0.0274   1.0000   0.2687
  -4.500  -0.2937   0.05324   0.04422  -0.0282   1.0000   0.2701
  -4.250  -0.2767   0.05237   0.04335  -0.0277   1.0000   0.2724
  -4.000  -0.2581   0.05153   0.04242  -0.0277   1.0000   0.2745
  -3.750  -0.2392   0.05084   0.04159  -0.0278   1.0000   0.2773
  -3.500  -0.2202   0.05030   0.04088  -0.0279   1.0000   0.2814
  -3.250  -0.2002   0.04988   0.04017  -0.0283   1.0000   0.2875
  -3.000  -0.1834   0.04975   0.04002  -0.0279   1.0000   0.2937
  -2.750  -0.1673   0.04991   0.04018  -0.0275   1.0000   0.3008
  -2.500  -0.1479   0.05003   0.03999  -0.0278   1.0000   0.3102
  -2.250  -0.1124   0.05178   0.04185  -0.0305   0.9920   0.3230
  -2.000  -0.0760   0.05343   0.04347  -0.0335   0.9799   0.3411
  -1.750  -0.0418   0.05494   0.04496  -0.0362   0.9655   0.3618
  -1.500  -0.0023   0.05682   0.04682  -0.0395   0.9478   0.3898
  -1.250   0.1193   0.05791   0.04819  -0.0510   0.8431   0.4634
  -1.000   0.1746   0.05813   0.04852  -0.0534   0.8055   0.5143
  -0.750   0.2242   0.05811   0.04855  -0.0555   0.7794   0.5670
  -0.500   0.2790   0.05754   0.04813  -0.0590   0.7581   0.6329
  -0.250   0.3356   0.05625   0.04809  -0.0629   0.7389   0.7990
   0.000   0.3918   0.05653   0.04799  -0.0684   0.7187   1.0000
   0.250   0.4261   0.05696   0.04815  -0.0694   0.6998   1.0000
   0.500   0.4563   0.05738   0.04839  -0.0696   0.6811   1.0000
   0.750   0.4860   0.05773   0.04860  -0.0696   0.6626   1.0000
   1.000   0.5159   0.05797   0.04873  -0.0695   0.6442   1.0000
   1.250   0.5471   0.05804   0.04871  -0.0693   0.6260   1.0000
   1.500   0.5804   0.05791   0.04849  -0.0691   0.6087   1.0000
   1.750   0.6372   0.05625   0.04676  -0.0703   0.5973   1.0000
   2.000   0.6585   0.05656   0.04702  -0.0691   0.5788   1.0000
   2.250   0.6785   0.05700   0.04742  -0.0679   0.5609   1.0000
   2.750   0.7610   0.05435   0.04467  -0.0674   0.5374   1.0000
   3.250   0.7733   0.05816   0.04846  -0.0643   0.5054   1.0000
   3.500   0.8573   0.05227   0.04250  -0.0652   0.5018   1.0000
   3.750   0.8418   0.05644   0.04667  -0.0629   0.4858   1.0000
   4.000   0.9859   0.04599   0.03609  -0.0680   0.4826   1.0000
   4.250   0.9335   0.05260   0.04276  -0.0627   0.4672   1.0000
   4.500   0.8543   0.06418   0.05442  -0.0593   0.4505   1.0000
   4.750   1.1156   0.04376   0.03358  -0.0707   0.4408   1.0000
   5.000   1.1917   0.04260   0.03218  -0.0761   0.4236   1.0000
   5.250   1.1451   0.04648   0.03629  -0.0679   0.4164   1.0000
   5.500   1.2082   0.04602   0.03565  -0.0717   0.4011   1.0000
   5.750   1.1778   0.04938   0.03919  -0.0657   0.3933   1.0000
   6.000   1.2208   0.04983   0.03955  -0.0673   0.3801   1.0000
   6.250   1.1539   0.05558   0.04556  -0.0589   0.3756   1.0000
   6.500   1.0888   0.06320   0.05337  -0.0534   0.3696   1.0000
   6.750   1.2972   0.05363   0.04321  -0.0671   0.3442   1.0000
   7.000   1.2242   0.05902   0.04893  -0.0576   0.3423   1.0000
   7.250   1.0359   0.07844   0.06877  -0.0488   0.3441   1.0000
   7.500   0.7443   0.12456   0.11509  -0.0601   0.3517   1.0000
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