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CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK YM-18 AIRFOIL (clarym18-il)
Reynolds number: 50,000
Max Cl/Cd: 7.57 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarym18-il-50000.txt
Download as CSV file: xf-clarym18-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-18 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3032   0.12202   0.11506  -0.0200   1.0000   0.3229
  -9.000  -0.3044   0.12039   0.11349  -0.0177   1.0000   0.3312
  -8.750  -0.3569   0.12194   0.11522  -0.0144   1.0000   0.3376
  -8.500  -0.3261   0.11710   0.11037  -0.0131   1.0000   0.3438
  -8.250  -0.3320   0.11568   0.10901  -0.0107   1.0000   0.3526
  -8.000  -0.3975   0.11737   0.11091  -0.0067   1.0000   0.3584
  -7.750  -0.3530   0.11198   0.10547  -0.0061   1.0000   0.3647
  -7.500  -0.6042   0.08742   0.08095  -0.0219   1.0000   0.2039
  -7.250  -0.6118   0.08376   0.07730  -0.0204   1.0000   0.2022
  -7.000  -0.6281   0.07907   0.07255  -0.0196   1.0000   0.1997
  -6.750  -0.6495   0.07304   0.06634  -0.0194   1.0000   0.1965
  -6.500  -0.6673   0.06647   0.05941  -0.0197   1.0000   0.1942
  -6.250  -0.6714   0.06162   0.05422  -0.0194   1.0000   0.1945
  -6.000  -0.6678   0.05798   0.05026  -0.0188   1.0000   0.1968
  -5.750  -0.6615   0.05441   0.04625  -0.0184   1.0000   0.2005
  -5.500  -0.6528   0.05062   0.04172  -0.0184   1.0000   0.2048
  -5.250  -0.6370   0.04989   0.04126  -0.0171   1.0000   0.2103
  -5.000  -0.6222   0.04822   0.03933  -0.0165   1.0000   0.2173
  -4.750  -0.6064   0.04622   0.03695  -0.0162   1.0000   0.2245
  -4.500  -0.5898   0.04555   0.03633  -0.0153   1.0000   0.2326
  -4.250  -0.5719   0.04405   0.03445  -0.0151   1.0000   0.2420
  -4.000  -0.5545   0.04350   0.03397  -0.0143   1.0000   0.2515
  -3.750  -0.5358   0.04252   0.03276  -0.0140   1.0000   0.2625
  -3.500  -0.5172   0.04195   0.03209  -0.0135   1.0000   0.2749
  -3.250  -0.4987   0.04137   0.03155  -0.0130   1.0000   0.2875
  -3.000  -0.4793   0.04081   0.03089  -0.0127   1.0000   0.3028
  -2.750  -0.4598   0.04038   0.03040  -0.0124   1.0000   0.3209
  -2.500  -0.3827   0.04129   0.03145  -0.0219   0.9765   0.3658
  -2.250  -0.3372   0.04148   0.03179  -0.0256   0.9615   0.4082
  -2.000  -0.2947   0.04171   0.03219  -0.0286   0.9459   0.4559
  -1.750  -0.2540   0.04197   0.03266  -0.0310   0.9291   0.5056
  -1.500  -0.2149   0.04224   0.03318  -0.0328   0.9122   0.5593
  -1.250  -0.1775   0.04249   0.03375  -0.0338   0.8963   0.6206
  -1.000  -0.1415   0.04275   0.03445  -0.0337   0.8818   0.6974
  -0.750  -0.1296   0.04275   0.03488  -0.0293   0.8677   0.7787
  -0.500   0.0037   0.04496   0.03718  -0.0445   0.8485   0.9709
  -0.250   0.0771   0.04528   0.03707  -0.0561   0.8315   1.0000
   0.000   0.0870   0.04537   0.03689  -0.0548   0.8172   1.0000
   0.250   0.1216   0.04567   0.03692  -0.0566   0.8038   1.0000
   0.500   0.1449   0.04600   0.03704  -0.0564   0.7887   1.0000
   0.750   0.1582   0.04652   0.03740  -0.0549   0.7725   1.0000
   1.000   0.1780   0.04710   0.03782  -0.0542   0.7568   1.0000
   1.250   0.2057   0.04760   0.03816  -0.0544   0.7419   1.0000
   1.500   0.2544   0.04767   0.03806  -0.0570   0.7300   1.0000
   2.000   0.2769   0.04948   0.03966  -0.0535   0.6977   1.0000
   2.250   0.2979   0.05027   0.04034  -0.0529   0.6837   1.0000
   2.500   0.3428   0.05019   0.04014  -0.0545   0.6735   1.0000
   2.750   0.3420   0.05191   0.04179  -0.0519   0.6583   1.0000
   3.000   0.3540   0.05333   0.04313  -0.0508   0.6464   1.0000
   3.250   0.3872   0.05375   0.04345  -0.0513   0.6369   1.0000
   3.500   0.3816   0.05613   0.04578  -0.0489   0.6242   1.0000
   3.750   0.4244   0.05610   0.04566  -0.0500   0.6170   1.0000
   4.000   0.4025   0.05977   0.04931  -0.0472   0.6061   1.0000
   4.250   0.4344   0.06047   0.04994  -0.0477   0.5991   1.0000
   4.500   0.4238   0.06369   0.05314  -0.0459   0.5906   1.0000
   4.750   0.4335   0.06575   0.05516  -0.0453   0.5834   1.0000
   5.250   0.4430   0.07100   0.06036  -0.0442   0.5731   1.0000
   5.500   0.4388   0.07414   0.06349  -0.0434   0.5686   1.0000
   5.750   0.4513   0.07639   0.06572  -0.0434   0.5641   1.0000
   6.000   0.4863   0.07756   0.06685  -0.0441   0.5588   1.0000
   6.250   0.4740   0.08153   0.07084  -0.0434   0.5576   1.0000
   6.500   0.4698   0.08507   0.07439  -0.0432   0.5572   1.0000
   6.750   0.4749   0.08840   0.07772  -0.0435   0.5581   1.0000
   7.000   0.4874   0.09165   0.08099  -0.0443   0.5593   1.0000
   7.250   0.3838   0.10247   0.09203  -0.0457   0.6555   1.0000
   7.500   0.3909   0.10500   0.09455  -0.0455   0.6509   1.0000
   7.750   0.3977   0.10647   0.09602  -0.0448   0.6394   1.0000
   8.000   0.4317   0.11080   0.10035  -0.0471   0.6339   1.0000
   8.250   0.4172   0.11102   0.10058  -0.0446   0.6232   1.0000
   8.500   0.4589   0.11567   0.10524  -0.0473   0.6159   1.0000
   8.750   0.4399   0.11579   0.10537  -0.0447   0.6056   1.0000
   9.000   0.4745   0.11985   0.10944  -0.0467   0.5979   1.0000
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