Design and performance of an experimental annular turbojet combustor with high-velocity- air admission through one wall
Experimental annular turbojet combustor with high velocity air admission through one wall
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Experimental annular turbojet combustor with high velocity air admission through one wall
Axial current distribution in exhaust of magnetic annular arc, examining effect of entrainment on thrust measurement
Scalar wave equation of annular membrane for origin symmetric motion and arbitrary initial and boundary conditions
Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack.
Effects of the Southern Hemisphere Annular Mode (SAM) and the extrapolar Southern Oscillation (SO) on surface temperature are quantified through regression analysis.
Performance of experimental annular turbojet combustors at simulated high altitude supersonic flight conditions
Cooling correlation for afterburner with annular cooling passage - combustion chamber wall temperatures
Annular flame-holder gutters and afterburner combustion efficiency
Neutralization of ion beams from engines of annular geometry
Effects of asymmetry in the heat flux of wall temperatures in the heat transfer along annular passages
The problem of turbulent flow heat transfer in a concentric circular tube annulus with fully developed velocity profile and constant heat rate per unit of length is considered. Experimentally obtained solutions are presented for the thermal entry length for a fluid with P(sub r) = 0·7. Asymptotic solutions (fully developed velocity and temperature profiles) are developed for a wide range of radius ratio, Reynolds number, and Prandtl number. The solutions are based on empirical velocity and eddy diffusivity profiles, and the validity of the solutions is demonstrated experimentally for P(sub r) = 0·7. A superposition method is demonstrated for solving the problem of asymmetric heating from the two surfaces of an annulus, and experimental data on asymmetric heating are presented which are in excellent agreement with the analysis. This paper is the third in a series (1, 2) culminating a four year study of heat transfer in annular passages.
Damping factor from flat annular ring baffles to prevent excessive propellant motion in space vehicle propellant tanks
Slosh-suppression effectiveness of annular ring baffles in spherical propellant tank
Performance characteristics at simulated high altitudes of prevaporizing annular turbojet combustor with low pressure loss
Annular linear induction or traveling wave electromagnetic pump
Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder
Tail-pipe fuel ratio, mass flow of combustion gas, and radial fuel flow distribution on cooling requirements of tail-pipe burner with annular cooling-air passage
Annular cascade investigation to provide design criteria for slotted rotor and stator blading