Axial flow compressor design computer programs incorporating full radial equilibrium. Part 1 - Flow path and radial distribution of energy specified /program 2/
Complete radial equilibrium flow computer program
Carmody, R. H.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Configuration design for specified pressure signature characteristics
Supersonic transport near field design concepts for plateau pressure signature to reduce sonic boom
F. Edward McLean↗
Axial flow compressor design computer programs incorporating full radial equilibrium. Part 2 - Radial distribution of total pressure and flow path or axial velocity ratio specified /program 3/
Axial flow compressor design computer programs incorporating radial distribution of total pressure and flow path or axial velocity ratio
Carmody, R. H.↗
The analysis of geometry and design-point performance of axial-flow turbines using specified meridional velocity gradients. Part 2 - Design examples
Computer program for design of axial flow turbines with velocity distribution gradients at stator and rotor exits
Carter, A. F.↗
Analysis of geometry and design-point performance of axial-flow turbines using specified meridional velocity gradients
Computer program for design point analysis of axial turbines
Carter, A. F.↗
Plant-canopy irradiance specified by the Duntley equations
Near IR radiation diurnal variations in corn canopy accounted for by Duntley equations for unidirectionally incident light propagation through diffusing medium
Allen, W. A.↗
Effect of randomly fluctuating pressure gradients, with arbitrarily specified power spectrum and probability density, on flow in channels
Randomly fluctuating, non-Gaussian pressure gradient effect on steady, incompressible channel flow
Perlmutter, M.↗
An approach for specifying limits on transients in digital equipments
Power line and signal line transients in digital systems
Birchfield, J. L.↗
Minimum-mass design of a plate-like structure for specified fundamental frequency
Minimum mass design of two dimensional plate-like structure with free vibration fundamental frequency or aeroelastic constraints, using optimal theory for extremum
Armand, J.-L.↗
Effect of randomly fluctuating pressure gradients, with arbitrarily specified power spectrum and probability density, on flow in channels
Random fluctuating longitudinal pressure gradient effect on steady incompressible channel flow for arbitrary power spectrum and probability density
Perlmutter, M.↗
Mechanical impedance and acoustic mobility measurement techniques of specifying vibration environments
Method has been developed for predicting interaction between components and corresponding support structures subjected to acoustic excitations. Force environments determined in spectral form are called force spectra. Force-spectra equation is determined based on one-dimensional structural impedance model.
Kao, G. C.↗
Long-range energy-state maneuvers for minimum time to specified terminal conditions.
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Parsons, M. G.↗
Nonlinear programming in design of control systems with specified handling qualities.
A method is described for using nonlinear programing in the computer-aided design of aircraft control systems. It is assumed that the quality of such systems depends on many criteria. These criteria are included in the constraints vector, and the design proceeds through a sequence of nonlinear programing solutions in which the designer varies the specification of sets of requirements levels. The method is applied to design of a lateral stability augmentation system (SAS) for a fighter aircraft, in which the requirements vector is chosen from the official handling-qualities specifications. Results are shown for several simple SAS configurations designed to obtain desirable handling qualities over all design flight conditions with minimum feedback gains.
Schy, A. A.↗
Effect of randomly fluctuating pressure gradients, with arbitrarily specified power spectrum and probability density, on flow in channels.
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Perlmutter, M.↗
Shape of porous cooled region for surface heat flux and temperature both specified.
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Siegel, R.↗
Characteristics of constrained optimum trajectories with specified range
Necessary conditions of optimality are derived for trajectories whose structure is limited to climb, steady cruise, and descent segments. The performance function consists of the sum of fuel and time costs, referred to as direct operating cost (DOC). The state variable is range to go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (500 n. mi. and less) a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust characteristics and on thrust constraints. If thrust is a free control variable along with airspeed, it is shown that such cruise segments will not generally occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally will occur. Computer calculations of typical short-range trajectories obtained about a 1% cost penalty for constraining the thrust.
Erzberger, H.↗
Minimum Altitude-Loss Soaring in a Specified Vertical Wind Distribution
Minimum altitude-loss flight of a sailplane through a given vertical wind distribution is discussed. The problem is posed as an optimal control problem, and several numerical solutions are obtained for a sinusoidal wind distribution.
Pierson, B. L.↗
Constrained optimum trajectories with specified range
The characteristics of optimum fixed-range trajectories whose structure is constrained to climb, steady cruise, and descent segments are derived by application of optimal control theory. The performance function consists of the sum of fuel and time costs, referred to as direct operating costs (DOC). The state variable is range-to-go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (500 n. mi. and less) a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust characteristics and on thrust constraints. If thrust is a free control variable along with airspeed, it is shown that such cruise segments will not generally occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally will occur. The performance difference between free thrust and constrained thrust trajectories has been determined in computer calculations for an example transport aircraft.
Erzberger, H.↗