Accession Number:

AD0270935

Title:

HYPERVELOCITY STAGNATION POINT HEAT TRANSFER

Descriptive Note:

Corporate Author:

GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s):

• SCALA,SINCLAIRE M.
• WARREN,WALTER R.

Report Date:

1961-10-01

Pagination or Media Count:

1.0

Abstract:

The results of a new theoretical analysis of the effects of ionization on hypervelocity stagnation point heat transfer, and experimental data obtained in a newly developed hypervelocity shock tube are presented for flight conditions ranging from orbital to superorbital velocities,AND COMPARED WITH EXISTING THEORIES. On the basis of the new theoretical results and the experimental data, it appears that the convective heat transfer rate encountered by a re-entry space vehicle entering the earths atmosphere at escape velocity is more than twice as large as predicted by existing theories. Author

Descriptors:

• *HEAT TRANSFER
• *HEMISPHERICAL SHELLS
• *HYPERSONIC CHARACTERISTICS
• AIR
• ATMOSPHERE ENTRY
• DIFFUSION
• DISSOCIATION
• ELECTRIC DISCHARGES
• GAS IONIZATION
• GASES
• HYPERSONIC FLOW
• LAMINAR BOUNDARY LAYER
• PARTICLES
• PLASMAS(PHYSICS)
• REENTRY VEHICLES
• ARTIFICIAL SATELLITES
• SHOCK TUBES
• SHOCK WAVES
• TRANSPORT PROPERTIES

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE