Jagadeesh, G and Reddy, NM and Nagashetty, K and Reddy, KPJ (2000) Forebody convective hypersonic heat transfer measurements over large-angle blunt cones. In: Journal of Spacecraft and Rockets, 37 (01). pp. 137-139.
PVJAIMP3537.pdf - Published Version
Restricted to Registered users only
Download (85Kb) | Request a copy
KNOWLEDGE of surface heat transfer rates for a vehicle con-. guration under hypersonic � ow is essential to quantify the heat-shieldingrequirement for the thermal protectionsystem (TPS) of space missions. Typically low-lift and high-drag bodies such as large-angle blunt cones are used as heat shields in modern aeroassisted orbital transfer vehicles1 (AOTVs). The development of these space vehicles requires a large volume of heat transfer data, which can also be used to validate computational uid dynamic codes. Although most of the AOTVs operate at very high velocities and high altitudes, the maximum convective heating will occur at conditions corresponding to continuum/near-continuum ow.2 Hence, carefullydesignedground-basedexperimentsin typicalhigh enthalpy continuum ow conditions will be very useful in designing the requisite TPS for such space missions. Previously, many authors have reported heat transfer measurements over large-angle blunt bodies.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||22 Jul 2009 07:48|
|Last Modified:||19 Sep 2010 04:58|
Actions (login required)