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A unique perspective of system integration is presented in terms of statistical design and analysis. Advanced statistical concepts are employed to quantify the variance of the statistical models as well as to specify model truncation error. Three models are developed for this study: 1) a supersonic wing section; 2) a supersonic turbojet system and; 3) an integrated supersonic wing section and supersonic turbojet. The three models are analyzed and separately and surrogate models are developed for each model independently using Design of Experiments and advanced statistical analyses. The individual surrogate models are statistically validated compared to their respective models. The individual wing and turbojet surrogate models are then used to estimate the performance of the combined wing and turbojet system surrogate model performance.

The effects of elevated acceleration fields on spray cooling heat transfer are discussed in this paper. Spray cooling has proven to be one of the most efficient methods of heat removal. This technology is being transitioned into more advanced applications, such as fighter aircraft that must withstand a wide range of variable acceleration-induced body forces. Heat transfer associated with closed-loop spray cooling will be affected by acceleration body forces, the extent of which is not yet known. To test these various effects, an eight-foot-diameter centrifuge table will be outfitted with a spray cooling system to test for the effects associated with elevated gravity.

The objective of this paper is to describe the design of an experiment that will examine the effects of elevated acceleration environments on a high-temperature, titanium-water loop heat pipe for actuator cooling. An experimental test setup has been designed for mounting a loop heat pipe on an 8-ft-diameter centrifuge table, which is capable of radial accelerations of up to 12 g's. A high-temperature PAO loop will interface the condenser of the loop heat pipe to simulate the rejection of the transported heat to an elevated temperature. In addition to LHP experimentation, a mathematical model has been developed for aerodynamic heating of highspeed aircraft. A flat plate at zero-incidence, used to model an aircraft wing, was subjected to sub- and supersonic flow to examine whether heat will be rejected or absorbed. The results of this analysis will be used to determine the condenser conditions of the loop heat pipe during centrifuge testing.

General thermodynamic analytical investigations on the primary components of aircraft power systems, as well as vehicle integration and mission considerations, have revealed that thermal management plays a key role in limiting payload size and performance. All power system components such as batteries, capacitors, power semiconductors, generators, pulsed power sources and beam conditioners have thermal design issues when their performance is pushed to deliver higher powers. Several technology driven thermal challenges need to be addressed in the development of these envisioned aircraft based weapon power systems. High power and high heat flux cooling requirements, coupled with a limited payload capacity, is one of the primary design challenges tackled in the development of this type of power system.

The objective of this paper is to design and fabricate a micro-cooler to provide integral cooling to electronics or Microelectromechanical Systems (MEMS) type components utilizing current MEMS technologies. A three-port capillary pumped loop (CPL) was analyzed and fabricated from silicon and quartz for this purpose. An analytical study of the device is presented in support of this design. This proves the feasibility of such a device, and thus the rationale for continuing its development.