An Analysis of Supersonic Aerodynamic Heating with Continuous Fluid Injection
Abstract
An analysis of the steady-state aerodynamic heating problem at high-supersonic speeds is made for two-dimensional flows with laminar boundary layers. The aerodynamic heating is shown to be reduced substantially by injecting a small amount of coolant through a porous surface into the boundary layer. The coolant injection acts in two ways to decrease the aerodynamic heating: First, and most important, the velocity profile is altered such that the rate at which heat is conducted to the surface is reduced and, second, the coolant absorbs an amount of heat which is a function of the difference in temperature between the surface and the coolant. The first effect provides the advantage of cooling by injection over that of simply using a coolant to absorb heat from the surface. Calculations of the stability of the laminar boundary layer show that for a wide range of high-speed flight conditions the boundary layer would remain laminar at all Reynolds numbers according to the stability-theory consideration. The analysis includes calculations of the cooling requirements and equilibrium surface temperatures for flat plates and for flat porous surfaces with several rates of fluid injection at Mach numbers from 5 to 15 and altitudes from sea level to 200,000 feet. Some calculations of the skin friction are also included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1949
- Accession Number
- ADA380483
Entities
People
- E. B. Klunker
- H. R. Ivey
Organizations
- National Aeronautics and Space Administration