An Approximate Method for the Calculation of Flow Field Profiles AeroThermo Sciences Dept., McDonnell Douglas Astronautics Company, St. Louis, MO

Format:

Conference/Event

Author/Creator:

Fivel, H. J., author.

Conference Name:

Intersociety Conference on Environmental Systems (1987-07-13 : Seattle, Washington, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1987

Summary:

A computer program designed to provide an economical, easy-to-use engineering analysis tool for computation of the shock shape, inviscid profiles, and aerodynamic heating over a wide variety of both simple and complex high speed vehicle configurations is discussed. The computer program, designated as AERHET, uses the Euler equation to estimate a three-dimensional inviscid surface streamline to be coupled with a boundary layer solution, using the axisymmetric analog technique to predict the heating rate. Comparisons between AERHET results and wind tunnel tests on a hyperboloid at zero incidence to simulate the Space Shuttle vehicle at angle of attack are presented, showing good agreement. AERHET results also are shown to agree approximately with the more rigorous calculations of a parabolized Navier Stokes computer program on a blunt cone configuration at angle of attack for a typical hypersonic flight condition

Notes:

Vendor supplied data

Publisher Number:

871481

Access Restriction:

Restricted for use by site license