The Downstream Influence Of Mass Transfer At The Nose Of A Slender Cone

Item

Title
The Downstream Influence Of Mass Transfer At The Nose Of A Slender Cone
Date
1961
Index Abstract
Contrails and DTIC condensed
Photo Quality
Incomplete
Report Number
WADD TR 60-892
Creator
Cresci, Robert J.
Libby, Paul A.
Corporate Author
Polytechnic Institute Of Brooklyn
Laboratory
Directorate of Materials and Processes
Extent
46
Identifier
AD0257807
AD0257807
Access Rights
OTS
Distribution Classification
1
Contract
AF 33(616)-5944
DoD Project
7364
DoD Task
73652
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
None
Report Availability
Full text available by request
Date Issued
1961-05
Abstract
The influence of localized mass transfer at the nose of a slender cone under hypersonic flow conditions was studied by experimental and theoretical means. Two gaseous coolants, nitrogen and helium are injected through a porous plug subtending a half angle of 30°. The effect of the mass transfer on the shock shape, pressure distribution, heat transfer and transition are investigated. The experimental work involved tests in the Mach number 8.0 tunnel at PIBAL. The theoretical analysis involved a study of the effect of mass transfer on the shock stand-off distance and leads to an inviscid flow parameter permitting the experimentally determined shock shape and pressure distribution to be extrapolated to other than test conditions and to other coolant gases. There is obtained the maximum value of this parameter resulting in no significant alteration of the pressure distribution on the cone and thus defining the flows in which boundary layer type of similarity applies.

Significant reductions in heat transfer are obtained with injection. Indeed with small amounts of helium injection the peak heating is found to occur downstream on the cone and to be an order of magnitude less than would occur at the stagnation point without mass transfer. With nitrogen early transition is found to occur so that local heating rates are actually increased over those prevailing at the same Reynolds number without injection.
Publisher
Wright-Patterson Air Force Base, OH : Directorate of Materials and Processes, Aeronautical Systems Division, Air Force Systems Command
Distribution Conflict
No
Type
report
Provenance
Lockheed Martin Missiles & Fire Control
Subject
Heat Transfer
Nose Cones
Conical Bodies
Hypersonic Flow
Sweat Cooling
Film Cooling
Helium
Diffusion
Hypersonic Wind Tunnels
Gas Flow
Laminar Boundary Layer
Coolants
Pressure
Nitrogen
Turbulent Boundary Layer
Boundary Layer
Shock Waves
Ablation
Format
46 pages ; 28 cm.