# 升力係數

## 定義

${\displaystyle C_{\mathrm {L} }\equiv {\frac {L}{q\,S}}={\frac {L}{{\frac {1}{2}}\rho u^{2}\,S}}={\frac {2L}{\rho u^{2}S}}}$  ,

${\displaystyle S_{aer}\equiv c\,s}$

${\displaystyle C_{\mathrm {L} ,\,aer}\equiv {\frac {L}{q\,c\,s}},}$

${\displaystyle S_{mar}=t\,s}$

${\displaystyle C_{\mathrm {L} ,\,mar}\equiv {\frac {L}{q\,t\,s}}}$

${\displaystyle C_{\mathrm {L} ,\,mar}\equiv {\frac {c}{t}}C_{\mathrm {L} ,\,aer}}$

## 翼型升力係數

${\displaystyle c_{\text{l}}={\frac {l}{q\,L}},}$

## 注釋

1. ^ Clancy, L. J. Aerodynamics. New York: John Wiley & Sons. 1975. Sections 4.15 & 5.4.
2. , and Doenhoff, Albert E. von: Theory of Wing Sections. Section 1.2
3. ^ Clancy, L. J.: Aerodynamics. Section 4.15
4. ^ Clancy, L. J.: Aerodynamics. Section 8.11
5. ^ Abbott, Ira H., and Von Doenhoff, Albert E.: Theory of Wing Sections. Appendix IV
6. ^ Clancy, L. J.: Aerodynamics. Section 8.2

## 參考資料

• L. J. Clancy (1975): Aerodynamics. Pitman Publishing Limited, London, ISBN 0-273-01120-0
• Abbott, Ira H., and Doenhoff, Albert E. von (1959): Theory of Wing Sections, Dover Publications New York, # 486-60586-8