Aerodynamic heating of parachutes

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

Performance improvement of arc heaters for aerodynamic wind tunnels

Mode of access: Internet.

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."

High temperature radome design techniques.

Caption title.

Coupled thermal, structural and vibrational analysis of a hypersonic engine for flight test

This paper describes a relatively simple and quick method for implementing aerodynamic heating models into a finite element code for non-linear transient thermal-structural and thermal-structural-vibrational analyses of a Mach 10 generic HyShot scramjet engine. The thermal-structural-vibrational response of the engine was studied for the descent trajectory from 60 to 26 km. Aerodynamic heating fluxes, as a function of spatial position and time for varying trajectory points, were implemented in the transient heat analysis. Additionally, the combined effect of varying dynamic pressure and thermal loads with altitude was considered. This aero-thermal-structural analysis capability was used to assess the temperature distribution, engine geometry distortion and yielding of the structural material due to aerodynamic heating during the descent trajectory, and for optimising the wall thickness, nose radius of leading edge, etc. of the engine intake. A structural vibration analysis was also performed following the aero-thermal-structural analysis to determine the changes in natural frequencies of the structural vibration modes that occur at the various temperatures associated with the descent trajectory. This analysis provides a unique and relatively simple design strategy for predicting and mitigating the thermal-structural-vibrational response of hypersonic engines. (C) 2006 Elsevier SAS. All rights reserved.

Wettability, Shrinkage and Color Changes of Araucaria angustifolia After Heating Treatment

The effects of thermal treatment on the wettability and shrink resistance of Araucaria angustifolia (Parana pine) were studied from 20 to 200 °C. The contact angles of water droplets on untreated and heat-treated samples were measured by the sessile drop method in the grain of heartwood and sapwood cut in the radial, longitudinal, and tangential directions. A significant increase of the contact angles was verified for the samples from room temperature to 120 °C, in particular in the radial and tangential directions; at higher temperatures, the contact angles assumed almost constant values. From 120 to 200 °C, the sapwood of Araucaria angustifolia showed better dimensional stability and lower thermal resistance when compared to the heartwood. Variations of color were also studied by using the CIELab system, which showed to be capable of accurately distinguishing samples treated at different temperatures.