John B. Miles

Skin-friction measurements in three-dimensional, supersonic shock-wave/boundary-layer interaction

The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 flow is presented. The model consisted of a sting-supported cylinder, aligned with the freestream flow, and a 20-deg half-angle conical flare offset 1.27 cm from the cylinder centerline. Surface oil flow, laser light sheet illumination, and spark schlieren photography were used to document the flow topology. Extensive surface-pressure and skin-friction measurements were made throughout the interaction region. A laser interterometric skin-friction instrument was employed to acquire the skin-friction data. Resolved skin-friction measurements of C fx and C fz were made within the highly swept three-dimensional separated regions. The skin-friction data will be of particular value for turbulence modeling and computational fluid dynamics validation

Thermal Analysis and Design of an Advanced Space Suit

The thermal dynamics and design of an advanced space suit are considered. A transient model of the advanced space suit design has been developed and implemented using MATLAB ® /Simulink, to help with sizing, with design evaluation, and with the development of an automatic thermal comfort control strategy. The model is described and the thermal characteristics of the advanced space suit are investigated including various parametric design studies. The steady-state performance envelope for the advanced space suit is dee ned in terms of the thermal environment and human metabolic rate and the transient response of the human-suit ‐minimum consumables portable life support system is analyzed.

Development And Implementation Of An Aerodynamic Holographic Interferometry System

An aerodynamic holographic interferometry system has been developed and adapted for use with an existing supersonic wind tunnel. The tunnel had a 25.4 cm wide by 38.1 cm high test section, was an air-operated blow-down facility, and was run at nominal conditions of Mach number equal 2.85, total temperature of 270° K, and total pressure of 1.7 and 3.4 atmospheres. The associated fluid dynamics investigation centered on the SW/BLI problem occuring at an axisymmetric compression corner, physically created by a cylinder/cone intersection. The cylinder had a 5.08 cm diameter and was used with interchangeable conic flares of 12.5°, 20°, and 30° [each with cylinder afterbodies]. Complementary laser velocimeter measurements and Navier-Stokes computations are presented in support of the accuracy of the holographic interferometry results. The interferometry systems is illuminated by an available Q-switched ruby laser, which is expanded in the object beam to 30.48 cm diameter at the wind tunnel test section. A 5 mw He-Ne laser was used for alignment. The system features three modules: laser and reference beam, object beam expansion, and holocamera module. The design yielded excellent dynamic stability as a result of structural rigidity and placement of spatial filters far downbeam. Thermal stability also proved adequate. The system was easy to operate, and allowed for use with ambient lighting. Also, the system was necessarily operated remotely because of wind tunnel access limitations during a run. Cost figures and detailed equipment schematics are included in the paper. Additionally, the paper includes discussion of the Abel integral inversion program used to determine density profiles in the axisymmetric flow field from the recorded photographs.