Numerical analysis of unsteady laminar boundary layers = 비정상 층류 경계층 유동의 수치해석

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Unsteady boundary layer equations are solved by a noniterative implicit numerical scheme which is second-order accurate both in time and space. The present numerical method provides initial data within the method itself by solving a reduced initial boundary value problem applicable at or very near the origin of a streamwise coordinate. The method has been applied to unsteady laminar boundary layers with large disturbance parameters such as transition to Falkner-Skan flow, oscillating Blasius flow, oscillating Stagnation-Point flow, constant accelerated flow and harmonically fluctuating boundary layer past a circular cylinder. The thermal effects are also considered in the boundary layers of the last application. Comparison with the existing data has demonstrated excellency of the present method both in accuracy and computer-time economy.
Advisors
Chang, Keun-Shikresearcher장근식researcher
Description
한국과학기술원 : 항공공학과,
Publisher
한국과학기술원
Issue Date
1983
Identifier
63625/325007 / 000811060
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 항공공학과, 1983.2, [ vii, 49 p. ]

URI
http://hdl.handle.net/10203/26569
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=63625&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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