Title: LAMINAR FLOW AT THE JUNCTURE OF TWO AEROPLANE COMPONENTS**Sponsored by U.S. Air Force under Contract AF33(616)-3168.
Abstract: This chapter provides an overview of the laminar flow at the juncture of two aeroplane components. The juncture can be designed so that the pressure gradients are two-dimensional for the forward portion of the wing, and the computation of the suction requirements for this region can be treated as for an isolated two-dimensional configuration. As a result of certain characteristics peculiar only to the region near the juncture of two airplane components, the approach to the problem of maintaining laminar flow past a juncture is necessarily somewhat different from the approach for isolated components. The difficulty stems from the fact that generally the pressure field on the surface of at least one of the intersecting components is three-dimensional in nature. The corresponding pressure gradients have strong components in the crossflow direction. Very little progress has been made along the line of calculating the boundary layer growth for such pressure gradients. Without such calculations, it is impossible to estimate accurately the suction requirements for a juncture. At the present time, therefore, the design for a juncture must be somewhat intuitive.
Publication Year: 1961
Publication Date: 1961-01-01
Language: en
Type: book-chapter
Indexed In: ['crossref']
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Cited By Count: 2
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