Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 364
Book Description
Scientific and Technical Aerospace Reports
Author: Government Reports Announcements & Index
Author: Experimental Studies of Shock-Wave/Wall-Jet Interaction in Hypersonic Flow
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781723575044
Category :
Languages : en
Pages : 234
Book Description
Experimental studies have been conducted to examine slot film cooling effectiveness and the interaction between the cooling film and an incident planar shock wave in turbulent hypersonic flow. The experimental studies were conducted in the 48-inch shock tunnel at Calspan at a freestream Mach number of close to 6.4 and at a Reynolds number of 35 x 10(exp 6) based on the length of the model at the injection point. The Mach 2.3 planar wall jet was generated from 40 transverse nozzles (with heights of both 0.080 inch and 0.120 inch), producing a film that extended the full width of the model. The nozzles were operated at pressures and velocities close to matching the freestream, as well as at conditions where the nozzle flows were over- and under-expanded. A two-dimensional shock generator was used to generate oblique shocks that deflected the flow through total turnings of 11, 16, and 21 degrees; the flows impinged downstream of the nozzle exits. Detailed measurements of heat transfer and pressure were made both ahead and downstream of the injection station, with the greatest concentration of measurements in the regions of shock-wave/boundary layer interaction. The major objectives of these experimental studies were to explore the effectiveness of film cooling in the presence of regions of shock-wave/boundary layer interaction and, more specifically, to determine how boundary layer separation and the large recompression heating rates were modified by film cooling. Detailed distributions of heat transfer and pressure were obtained in the incident shock/wall-jet interaction region for a series of shock strengths and impingement positions for each of the two nozzle heights. Measurements were also made to examine the effects of nozzle lip thickness on cooling effectiveness. The major conclusion from these studies was that the effect of the cooling film could be readily dispersed by relatively weak incident shocks, so the peak heating in the recompression region was not sig...
NASA SP.
Author: Lasers and Masers
Author: Experimental Studies of Hypersonic Shock-Wave Boundary-Layer Interactions
Author: National Aeronautics and Space Adm NasaPublisher:
ISBN: 9781730766190
Category :
Languages : en
Pages : 66
Book Description
Two classes of shock-wave boundary-layer interactions were studied experimentally in a shock tunnel in which a low Reynolds number, turbulent flow at Mach 8 was developed on a cold, flat test surface. The two classes of interactions were: (1) a swept interaction generated by a wedge ('fin') mounted perpendicularly on the flat plate; and (2) a two-dimensional, unseparated interaction induced by a shock impinging near an expansion corner. The swept interaction, with wedge angles of 5-20 degrees, was separated and there was also indication that the strongest interactions prossessed secondary separation zones. The interaction spread out extensively from the inviscid shock location although no indication of quasi-conical symmetry was evident. The surface pressure from the upstream influence to the inviscid shock was relatively low compared to the inviscid downstream value but it rose rapidly past the inviscid shock location. However, the surface pressure did not reach the downstream inviscid value and reasons were proposed for this anomalous behavior compared to strongly separated, supersonic interactions. The second class of interactions involved weak shocks impinging near small expansion corners. As a prelude to studying this interaction, a hypersonic similarity parameter was identified for the pure, expansion corner flow. The expansion corner severely damped out surface pressure fluctuations. When a shock impinged upstream of the corner, no significant changes to the surface pressure were found as compared to the case when the shock impinged on a flat plate. But, when the shock impinged downstream of the corner, a close coupling existed between the two wave systems, unlike the supersonic case. This close coupling modified the upstream influence. Regardless of whether the shock impinged ahead or behind the corner, the downstream region was affected by the close coupling between the shock and the expansion. Not only was the mean pressure distribution modified but the un...
Heat, Mass, and Momentum Transfer
Author: Warren M. RohsenowTheoretical Investigations of the Ablation of a Glass-type Heat Protection Shield of Varied Material Properties at the Stagnation Point of a Re-entering IRBM
Author: Ernst W. AdamsPublisher:
ISBN:
Category : Materials
Languages : en
Pages : 76
Book Description
Handbook of Chemical Engineering Calculations
Author: Nicholas P. ChopeyPublisher: McGraw-Hill Companies
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 580
Book Description
If solving chemical engineering problems quickly and accurately is key to your work, here's an invaluable info-packed resource: McGraw-Hill's Handbook of Chemical Engineering Calculations. Fully revised and expanded, this Third Edition delivers step-by-step procedures for performing a wide array of chemical engineering calculations -- along with fully worked-out examples that help you avoid costly errors. Book jacket.
A Flight Determination of the Tolerable Range of Effective Dihedral on a Conventional Fighter Airplane
Author: Charles J. LiddellPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
A conventional fighter airplane was equipped with a special device for varying the effective dihedral in flight. A survey of pilot's opinions was made to determine which values of effective dihedral were intolerable. The relation between the findings and the present Air Force-Navy stability and control specifications is discussed.