Accession Number:

AD1085761

Title:

The Effect of Multi-mode Induced Transition in a Hypersonic Boundary Layers

Descriptive Note:

Technical Report,30 Sep 2015,29 Sep 2018

Corporate Author:

HOWARD UNIV WASHINGTON DC WASHINGTON United States

Personal Author(s):

• Smith,Sonya

Report Date:

2019-04-02

Pagination or Media Count:

19.0

Abstract:

This study extends the work of Smith to Mach numbers indicative of the hypersonic flight regime and correlate the results to the occurrence of transition. The existing model uses PSE to capture the fully nonlinear interaction of modes in a low-speed, non-reacting, compressible boundary layer. It has the capability to calculate the contributions to surface heating and skin friction from the interaction of homogeneous e.g. first-modesecond-mode and inhomogeneous mode interaction e.g. second-modecrossflow. This approach captures the more realistic conditions that occur in-flight.

Descriptors:

• skin friction
• boundary layer
• hypersonic flight
• mach number
• flight

Subject Categories:

• Fluid Mechanics
• Military Aircraft Operations

Distribution Statement:

APPROVED FOR PUBLIC RELEASE