Masashi Matsumoto

Validation studies of scramjet nozzle performance

Thrust by scramjet nozzles was measured using a high-temperature gas flow with Mach 2.5 and a total temperature of 3100 K by combustion of monomethyl-hydrazine (MMH) and nitrogen tetraoxide (NTO). Wall pressure on the nozzles was monitored to estimate the pressure force on the nozzles. Series of cold nitrogen (N2) flow tests were also conducted using the same nozzles. An inviscid two-dimensional code was able to reproduce nozzle performance of the cold N2 flow. The calculations with chemical kinetics also predicted the experimental results of the MMH/NTO flow within an error of 3.6%. Kinetic, two-dimensional and friction losses in the scramjet nozzles were identified for the nozzle, and the scale effects of the nozzle performance of H2-fueled engines are discussed.

Estimating the Temperature Dependence of Pressure Sensitive Paints

The present paper describes the temperature dependence of the pressure sensitive paints in the pressure range of 1101.3kPa, and the wall temperature range of 263303K. The pressure sensitive paints investigated in the present work are PtOEP, PtTFPP, H2TFPP, H2TCPP, H2TSPP, and H2TTMAPP, and painted on a commercial porous silica thin-layer chromatography (TLC) plate. We estimate the uncertainty of the measured pressure value due to the change in the wall temperature. As a result, the uncertainty of H2TFPP is smaller than 3.5kPa per Kelvin in the present measuring range, and this paint is the most useful paint among the PSPs tested in the present work for measuring the surface pressure of the aerodynamic body on which there are temperature distributions.

Fundamental Experiment on Luminescence Characteristics of Pressure Sensitive Paint

A fundamental experiment of the temperature characterisitc of the pressure sensitive paint (PSP) to a continuous change in pressure is performed. As the results, for fixed temperature, as the pressure decreases, the paints brightness increases and for high temperature the brightness decreases. Also, as temperature increases, relative intensity decreases, and relative sensitivity to pressure changes increases. Furthermore, the characteristic of the response of the PSP to a step change in pressure is presented and the time constant is estimated.

Performance of a scramjet nozzle in hypersonic flight conditions

Performance of a scramjet nozzle (Singlc Expanded Ramp Nozzle) was estimated in relation to exteinal conditions along a corridor having flight paths with a constant dynamic pressure. The flow conditions in an airlramc-intcgratcd scramjet engine were calculated with a quasi-one-dimensional calculation mcthod. Thc cxpansion ratio of the nozzle was set at 5. The back pressure of the nozzle was assumed to be that behind the shock wave generated at the nose of the vehicle. The results show that thc flight conditions of the nozzle along each path did not differ significantly from each other. The nozzle worked in underexpanded conditions but suffered from overexpansion loss along the corridor. Nomenclature A Cf = thrust coefficient C* = characteristic velocity Isp 2) MOC = method of characteristic NPR = nozzle pressure ratio Pb = back pressure of SERN Ps = static pressure of the free strcam and outer surface of a vehicle Po = total pressure of nozzle flow Pw = static(wal1) pressure in scramjet cnginc and SERN 9 = dynamic pressure of the frce stream SERN = single expanded ramp nozzle Vei = exhaust velocity of isentropic expansion = area of the scramjet engine and SERN = specific impulse (x-componcnt i n Figurc nozzle TDK = two-dimensional kinetic codc E = nozzle expansion ratio Y = specific heat ratio Subscripts ideal = isentropic expansion nozzlc 0 2 nose of vehicle 5 engine of the inlct of SERN = free stream condition , = behind the shock wave gencratcd at thc = exit of the internal nozzle of sclaiiijct ?Researcher, Ramjet Combustion Laboratory.

PIV Measurement of Supersonic Swirling Jet

Head, Ramjet Combustion Laboratory.

Performance Variation of Scramjet Nozzle at Various Nozzle Pressure Ratios

Research Engineer, Fluid Dynamics and Combustion Dcpartmcnt, Rcscarch Institute(Toyosu). Copyfight