H. E. Neumann
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Dynamic distortion in a short s-shaped subsonic diffuser with flow separation Open
An experimental investigation of the time varying distortion at the diffuser exit of a subscale HiMAT forebody and inlet was conducted at Mach 0.9 in the Lewis 8 by 6 foot Supersonic Wind Tunnel. A transitory separation was detected within…
An analytical and experimental comparison of the flow field of an advanced swept turboprop Open
An argon ion laser velocimeter with four beams was used to measure the detailed flow-field of an advanced eight blade propeller with 45% of tip sweep in an 8x6 foot supersonic wind tunnel. Data were obtained at a free stream Mach number of…
An analytical and experimental study of a short S-shaped subsonic diffuser of a supersonic inlet Open
A subscale HiMAT forebody and inlet was investigated over a range of Mach numbers to 1.4. The inlet exhibited a transitory separation within the diffuser but steady state data indicated reattachment at the diffuser exit. A finite differenc…
Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction Open
A full-scale, mixed-compression inlet was designed for operation with the TF30-P-3 turbofan engine and tested at Mach numbers of 2.5 and 2.0. The two-cone axisymmetric inlet had minimum internal contraction consistent with high total press…
Some characteristics of turbulent boundary layers in rapidly accelerated flows Open
An analysis of time-mean-turbulent boundary layer velocity profiles measured in a rapidly accelerating flow suggests that the outer region of the velocity profiles consists of essentially inviscid, rotational flow. The extent of this invis…
Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent Open
Limitations on fully developed laminar flows due to compressibility and property variations are examined. The cases, for liquids and for gases, wherein such motions are "exact" are determined and solutions are given. For more general condi…
Performance of a High-solidity High-pressure-ratio Transonic Rotor Open
A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 10…
Performance of a supersonic rotor having high mass flow Open
Report presenting testing of a 14-inch supersonic mixed-flow rotor with a supersonic leading edge and an inlet radius ratio of 0.52, which was designed for impulse operation and uniform work output and tested in Freon-12. Results regarding…