Author: Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 104
Book Description
Hypersonic Free Flight Research: Investigations of heat trasfer and aerodynamic stability, by O. R. Burggraf
Author: Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 104
Book Description
Hypersonic Free Flight Research: Investigations of heat trasfer and aerodynamic stability, by O. R. Burggraf
Author: Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 100
Book Description
Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies
Author: James E. BrunkPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 168
Book Description
Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
Hypersonic Free Flight Research: Instrumentation evaluation and data analysis, by R. W. Bogle and R. J. Magnus
Author: Robert Worthington BoglePublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 56
Book Description
Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies
Author: James E. BrunkThe High Temperature Aspects of Hypersonic Flow
Author: Wilbur C. NelsonPublisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
Book Description
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Hypersonic Research Summary
Author: G. J. FabianPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 64
Book Description
The program areas included in this report are early work on the Wave Superheater and related research on Chemical Nonequilibrium in High-temperature Gas Flows, a Radiation Probe, Sound Propagation in an Excited of Dissociated Gas, Boundary Layer Phenomena in High-Temperature Gas Flows, and Molecular Interaction at High Temperatures.
U.S. Government Research Reports
Author: Review of Hypersonic Research
Author: Seymour M. BogdonoffPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 16
Book Description
Hypersonic Aerothermodynamics
Author: John J. BertinPublisher: AIAA
ISBN: 9781563470363
Category : Science
Languages : en
Pages : 644
Book Description
A modern treatment of hypersonic aerothermodynamics for students, engineers, scientists, and program managers involved in the study and application of hypersonic flight. It assumes an understanding of the basic principles of fluid mechanics, thermodynamics, compressible flow, and heat transfer. Ten chapters address: general characterization of hypersonic flows; basic equations of motion; defining the aerothermodynamic environment; experimental measurements of hypersonic flows; stagnation-region flowfield; the pressure distribution; the boundary layer and convective heat transfer; aerodynamic forces and moments; viscous interactions; and aerothermodynamics and design considerations. Includes sample exercises and homework problems. Annotation copyright by Book News, Inc., Portland, OR