Aerodynamic heating of parachutes

"Contract 33 (616)-3572. Project no. 7320.

Large carbon cluster thin film gauges for measuring aerodynamic heat transfer rates in hypersonic shock tunnels

Different types of Large Carbon Cluster (LCC) layers are synthesized by a single-step pyrolysis technique at various ratios of precursor mixture. The aim is to develop a fast responsive and stable thermal gauge based on a LCC layer which has relatively good electrical conduction in order to use it in the hypersonic flow field. The thermoelectric property of the LCC layer has been studied. It is found that these carbon clusters are sensitive to temperature changes. Therefore suitable thermal gauges were developed for blunt cone bodies and were tested in hypersonic shock tunnels at a flow Mach number of 6.8 to measure aerodynamic heating. The LCC layer of this thermal gauge encounters high shear forces and a hostile environment for test duration in the range of a millisecond. The results are favorable to use large carbon clusters as a better sensor than a conventional platinum thin film gauge in view of fast responsiveness and stability.

Performance improvement of arc heaters for aerodynamic wind tunnels

Mode of access: Internet.

Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow

In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow

In hypersonic flights, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling gas turbine engine, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt nosed spacecraft flying at Mach number 6.56 and 40 degree angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. Computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared each other. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

Instrumentation for magnetoaerodynamic heat transfer.

"Prepared for the Air Force Ballistic Missile Division, Headquarters Air Research and Development Command, under Contract AF(647)-309, Thermonuclear Propulsion Research."

Thermal effects on static aeroelastic stability and control.

v. 1. Methods of predicting structural temperatures due to aerodynamic heating, by A. H. Blessing.--v. 2. Aerodynamics, by J. R Batt.--v. 3. Experimental and analytical methods for the determination of thermally-affected wing deflectional behavior, by R. H. Gallagher.--v. 3. sup. Description and results of tests conducted to determine the thermally affected behavior of corrugated multiweb wing structures, by J. F. Quinn.

Preliminary analysis of the capabilities of a composite slab for an advanced heat-sink design /

"January 1961."

A study of the overall problems of the true-temperature, hypersonic wind tunnel having semi-continuous operation and the preferred methods of solution.

"Supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P. O. 7S4899-R. Purdue Research Foundation. Research project no. 1717. Project Ae-33.

A 50-megawatt arc heater: scaling parameters and performance prediction

"Project No. 1426, Task No. 142612."

Recent developments connected with the hypersonic facility of the Polytechnic Institute of Brooklyn. Pt. I: Tests of the compression heater. Pt. II: Aspects of the design, construction and installation of a multiple-outlet collector for the convection heater.

Mode of access: Internet.

Helium injection into the boundary layer at an axisymmetric stagnation point

"Contract no. AF 33(616)-7661, Project no. 7064, Task no. 70169."

Study of infrared emission in heated air; annual report, July 1960-June 1961,

"This report covers work performed under Bendix Aviation Corporation Purchase Order C 303681 G, Subcontract SD-59-2 under Army Ordnance Prime DA-11-022-ORD-3130."

An experimental study of the effect of mass injection at the stagnation point of a blunt body,

"Army Ordnance contract no. DA-04-495-Ord-19."

Optimum shape for transpiration-cooled nosetip of a re-entry vehicle /

"Technical report AFFDL-TR-78-147. Final report for period October 1974-June 1978."