Performance and stall limits of a YTF30-P-1 turbofan engine with uniform inlet flow
Performance and stall limits of YTF30-P-1 turbofan engine with uniform compressor inlet flow
Braithwaite, W. M.↗
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Stall and distortion investigation of a YTF30- p-1 turbofan engine.
Steady state and dynamic distortion influence on performance and stall of turbofan engine, discussing compressor instrumentation, tests and simulation data
Povolny, J. H.↗
Performance and stall limits of an afterburner-equipped turbofan engine with and without inlet flow distortion
Performance and stall limits of afterburner-type turbofan engine with and without inlet flow distortion
Abdelwahab, M.↗
Dynamic analysis of XB-70-1 inlet pressure fluctuations during takeoff and prior to a compressor stall at Mach 2.5
Inlet pressure fluctuation in XB-70 aircraft during takeoff and prior to compressor stall at Mach 2.5
Martin, R. A.↗
Dynamic stall simulation problems
Dynamic airfoil stall simulation in wind tunnels, considering pitch rate, Reynolds number, oscillation and test equipment effects
Ericsson, L. E.↗
Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-tip ratio single-stage compressor. Volume 1 - Data and performance report
Experimental data and performance of honeycomb rotor shroud configuration to improve stall margin of 0.5 hub tip ratio single stage compressor
Oscarson, R. P.↗
Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-tip ratio single-stage compressor. Volume 2 - Data supplement
Flow distribution data for solid and honeycomb rotor shrouds to improve stall margin of 0.5 hub tip ratio single stage compressor
Oscarson, R. P.↗
Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction
Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
Burstadt, P. L.↗
Effects of engine inlet disturbances on engine stall performance
Effects of engine inlet disturbances on engine stall performance
Burcham, F. W., Jr.↗
Utilization of a fixed base simulator to study the stall and spin characteristics of fighter airplanes
Feasibility of using fixed simulator to determine stall and spin characteristics of fighter aircraft
Adams, M. S.↗
Experimental investigation of the effect of screen induced total pressure distortion on turbojet stall margin
Effect of circumferential, radial, and combined pressure distortions on stall margin of J-85 engine
Burstadt, P. L.↗
A design summary of stall characteristics of straight wing aircraft
Computer program used for design criteria of stall characteristics of straight wing aircraft
Kisielowski, E.↗
Analytical investigation of the effects of blade flexibility, unsteady aerodynamics, and variable inflow on helicopter rotor stall characteristics
Analytical investigation of effects of blade flexibility, unsteady aerodynamics, and variable inflow on helicopter rotor stall characteristics
Bellinger, E. D.↗
Detailed aerodynamic measurements on a model rotor in the blade stall regime
Retreating blade stall experiments on model helicopter rotor, considering series of pressure distribution and boundary layer events
Fisher, R. K., Jr.↗
Surface temperature effect on subsonic stall.
Results of an analytical and experimental study of boundary layer flow over an aerodynamic surface rejecting heat to a cool environment. This occurs following reentry of a Space Shuttle vehicle. Analytical studies revealed that a surface to freestream temperature ratio, greater than unity tended to destabilize the boundary layer, hastening transition and separation. Therefore, heat transfer accentuated the effect of an adverse pressure gradient. Wind tunnel tests of a 0012-64 NACA airfoil showed that the stall angle was significantly reduced while drag tended to increase for freestream temperature ratios up to 2.2.
Macha, J. M.↗
Theory/test correlation of helicopter rotor blade element airloads in the blade stall regime
The effects of stall on a rotor blade element in a three-dimensional rotating environment was investigated. The model rotor test provided blade element airloads and local boundary layer flow characteristics at the three-quarter blade radius position for a wide range of rotor operating conditions. A description of the test program and the test results are presented.
Bobo, C. J.↗
Helicopter gust response characteristics including unsteady aerodynamic stall effects
The results of an analytical study to evaluate the general response characteristics of a helicopter subjected to various types of discrete gust encounters are presented. The analysis employed was a nonlinear coupled, multi-blade rotorfuselage analysis including the effects of blade flexibility and unsteady aerodynamic stall. Only the controls-fixed response of the basic aircraft without any aircraft stability augmentation was considered. A discussion of the basic differences between gust sensitivity of fixed and rotary wing aircraft is presented. The effects of several rotor configuration and aircraft operating parameters on initial gust-induced load factor and blade vibratory stress and pushrod loads are discussed.
Arcidiacono, P. J.↗
Prediction of compressor stall for distorted and undistorted flow by use of a multistage compressor simulation on the digital computer
A simulation technique is presented for the prediction of compressor stall for axial-flow compressors for clean and distorted inlet flow. The simulation is implemented on the digital computer and uses stage stacking and lumped-volume gas dynamics. The resulting nonlinear differential equations are linearized about a steady-state operating point, and a Routh-Hurwitz stability test is performed on the linear system matrix. Parallel compressor theory is utilized to extend the technique to the distorted inlet flow problem. The method is applied to the eight-stage J85-13 compressor.
Daniele, C. J.↗