Accession Number:

AD0687808

Title:

SECOND ORDER BOUNDARY LAYER THEORY FOR TWO-DIMENSIONAL AND AXIALLY SYMMETRIC FLOW (Grenzschichttheorie Zweiter Ordnung fuer Ebene und Achsensymmetrische Hyperschallstroemung)

Descriptive Note:

Corporate Author:

ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)

Personal Author(s):

Report Date:

1969-02-01

Pagination or Media Count:

19.0

Abstract:

It is shown that there is an interaction between pressure gradients normal and parallel to the surface in supersonic flows and that the effect of longitudinal curvature increases strongly with Mach number. The second order boundary layer equations and the matching conditions with the inviscid flow are discussed. As well as longitudinal curvature, transverse curvature and variations in stagnation pressure and enthalpy, are considered as second order effects. Integral relationships of the boundary layer equations momentum, energy equation, etc. are given. The effects are demonstrated by a numerical example of a laminar boundary layer profile and possibilities for an approximate solution of the equations are discussed.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE