Accession Number:

ADA280165

Title:

Heating Analysis for the Pioneer Venus Multiprobe Mission

Descriptive Note:

Technical memo.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s):

• Sutton, Kenneth

Report Date:

1974-07-01

Pagination or Media Count:

31.0

Abstract:

Results are presented for the fully-coupled, radiating flow field around the entry probes from a detailed calculation which includes equilibrium chemistry, nongray radiative transport, ablation product-injection, and a laminar or turbulent boundary layer. These results show that the radiative flux toward the body is attenuated in the boundary layer at downstream regions of the body as well as at the stagnation point and that, even when radiation absorption by ablation products is accounted for, the radiative heating rates along the downstream regions of the body can, under certain conditions, exceed the stagnation-point values. It is also shown that, for Venusian entry, the spectral distribution of radiative flux and the magnitude of radiation absorption by ablation products depend strongly on entry velocity, and that the state of the boundary layer i.e., laminar or turbulent can significantly influence the amount of ablation product absorption or emission that occurs in various spectral regions. Results from a series of radiative, inviscid calculations are also presented. Venusian entry, Radiative heating, Thermodynamics and combustion, Fluid mechanics, Space vehicles.

Descriptors:

• *SPACECRAFT
• *RADIATIVE TRANSFER
• *AEROTHERMODYNAMICS
• *VENUS(PLANET)
• *SPACE MISSIONS
• VELOCITY
• HEAT TRANSFER
• ATMOSPHERE ENTRY
• THERMODYNAMICS
• COMBUSTION
• RADIATION ABSORPTION
• STAGNATION POINT
• FLUID MECHANICS
• LAMINAR FLOW
• SPECTRAL ENERGY DISTRIBUTION
• FLOW FIELDS
• TURBULENT BOUNDARY LAYER
• BOUNDARY LAYER
• DISTRIBUTION
• ABLATION
• PROBES

Subject Categories:

• Fluid Mechanics
• Thermodynamics
• Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE