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Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Description: Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date: July 7, 1955
Creator: Hamrick, Joseph T. & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department

Experimental study of effect of vaneless-diffuser diameter on diffuser performance

Description: Report presenting an investigation of the diameter of vaneless diffusers and how it affects the variations in compressor and diffuser efficiency. The primary efficiency losses occurred in the vicinity of the diffuser entrance and exit. The effect of diffuser diameter was very slight on nearly all characteristics studied.
Date: October 1948
Creator: Bradshaw, Guy R. & Laskin, Eugene B.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of cone-type diffusers designed for minimum spillage at inlet

Description: Report presenting a preliminary investigation of cone-type diffusers designed for minimum spillage at the inlet during operation in the supersonic tunnel at Mach number 1.85. Pressure recoveries of a series of stationary cones with included angles from 20 degrees to 60 degrees were investigated. Results regarding the pressure recovery with stationary cones and pressure recovery of movable-cone configurations are provided.
Date: May 3, 1948
Creator: Luidens, Roger W. & Hunczak, Henry
Partner: UNT Libraries Government Documents Department

Method of designing vaneless diffusers and experimental investigation of certain undetermined parameters

Description: Report presenting a method of designing vaneless diffusers using data given for simple conical diffusers. A family of diffusers with three different cone angles and the same throat height was designed and experimentally studied. A second set of diffusers with varying throats with the best cone angle was also investigated.
Date: September 1947
Creator: Brown, W. Byron & Bradshaw, Guy R.
Partner: UNT Libraries Government Documents Department

Investigation of the effect of short fixed diffusers on starting blowdown jets in the Mach number range from 2.7 to 4.5

Description: Report presenting an investigation at several Mach numbers to determine the effect of short fixed convergent-divergent wedge diffusers on the starting characteristics of blowdown jets exhausting to the atmosphere. Results regarding the boundary-layer separation on nozzle contour, results of the testing, and analysis of flow during the starting process are provided.
Date: January 1956
Creator: Moore, John A.
Partner: UNT Libraries Government Documents Department

High Mach number, low-cowl-drag, external-compression inlet with subsonic dump diffuser

Description: Report presenting an investigation of a zero-cowl-drag, all-external-compression inlet with an abrupt area discontinuity or subsonic dump diffuser for high Mach number application. Results regarding the diffuser performance characteristics, effect of spike retraction, a comparison with other inlets, and some theoretical calculations related to the results are provided.
Date: May 12, 1958
Creator: Connors, James F. & Flaherty, Richard J.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of a translating cowl technique for improving take-off performance of a sharp-lip supersonic diffuser

Description: A preliminary investigation was conducted in quiescent air on a translating cowl technique for improving the take-off performance of a sharp-lip supersonic diffuser. The technique consists of cutting the cowling in a plane normal to its axis and then translating the forepart of the cowling in the forward direction. The leading edge of the fixed portion of the cowling is rounded. Appreciable improved inlet performance was obtained with a cowling translation corresponding to a gap of only 1/4 inlet radius.
Date: November 28, 1951
Creator: Cortright, Edgar M., Jr.
Partner: UNT Libraries Government Documents Department

Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Description: Report presenting a full-scale, free-jet investigation to determine the performance of a side-inlet supersonic diffuser designed for a flight Mach number of 2.75. Several internal modifications made to improve diffuser-outlet flow uniformity were also evaluated. Results regarding the general characteristics of the diffuser and effect of diffuser modifications on flow distribution are provided.
Date: March 28, 1955
Creator: Farley, John M. & Seashore, Ferris L.
Partner: UNT Libraries Government Documents Department

The use of perforated inlets for efficient supersonic diffusion

Description: Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date: September 1956
Creator: Evvard, John C. & Blakey, John W.
Partner: UNT Libraries Government Documents Department

The use of perforated inlets for efficient supersonic diffusion

Description: Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date: June 25, 1947
Creator: Evvard, John C. & Blakey, John W.
Partner: UNT Libraries Government Documents Department

Design and performance of family of diffusing scrolls with mixed-flow impeller and vaneless diffuser

Description: A family of diffusing scrolls was designed for use with a mixed-flow impeller and a small-diameter vaneless diffuser. The design theory, intended to maintain a uniform pressure around the scroll inlet, permits determination of the position of scroll cross sections of preassigned area by considering the radial variation in fluid density and the effects of friction along the scroll. Inasmuch as the design method leaves the cross-sectional shape undetermined, the effect of certain variations in scroll shape was investigated by studying scrolls having angles of divergence (of the scroll walls downstream of the entrance section) of 24 degrees, 40 degrees, and 80 degrees. A second 80 degree scroll was of asymmetrical construction and a third was plaster-cast instead of sand-cast. Each scroll was tested as a compressor component at actual impeller tip speeds of 700 to 1300 feet per second from full throttle to surge.
Date: October 1947
Creator: Brown, W. Byron & Bradshaw, Guy R.
Partner: UNT Libraries Government Documents Department

Comparative performance of two vaneless diffusers designed with different rates of passage curvature for mixed-flow impellers

Description: Report presenting an investigation of the effect of diffuser performance of the passage curvature of two vaneless diffusers designed with a 6 degree equivalent-cone divergence angle along a logarithmic-spiral path in combination with two mixed-flow impellers. The peak of overall adiabatic efficiency is compared with the corresponding diffuser efficiency. Results regarding the variation of diffuser efficiency with load-coefficient parameter and peak overall adiabatic efficiencies and corresponding diffuser efficiencies of the two compressors are provided.
Date: November 1947
Creator: Barina, Frank J.
Partner: UNT Libraries Government Documents Department

Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85

Description: Report presenting an experimental investigation at a Mach number of 3.85 in the supersonic wind tunnel to study the flow patterns at the throat of a two-dimensional single-shock diffuser and to evaluate qualitatively several schemes for improving the turning conditions. Schileren observations were made for supercritical inlet operation and conditions of maximum total-pressure recovery.
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department

Effects of shock-boundary-layer interaction on the performance of a long and a short subsonic annular diffuser

Description: Report presenting an investigation to determine the effects on performance of positioning normal shocks in or upstream of both a long and a short subsonic annular diffuser. Results regarding the entrance flow conditions, performance for subsonic-entrance flows, and performance with choked- and supersonic-entrance flows are provided.
Date: April 15, 1958
Creator: Wood, Charles C. & Henry, John R.
Partner: UNT Libraries Government Documents Department

Summary of subsonic-diffuser data

Description: Report presenting a review of subsonic-diffuser data, which was reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. The report is divided into the following sections: performance at low speeds, the effect of increasing the inlet speed up to choking Mach numbers, illustrations of the effectiveness of boundary-layer controls, and illustrations of the effects of distorted inlet velocity distributions at subsonic speeds.
Date: October 12, 1956
Creator: Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
Partner: UNT Libraries Government Documents Department

The effect of initial rate of subsonic diffusion on the stable subcritical mass-flow range of a conical shock diffuser

Description: Report presenting results of a systematic study in the 8- by 6-foot supersonic wind tunnel to determine the effect that area distribution in the subsonic diffuser might have on stability and overall performance of conical-type supersonic diffusers. Drag, pressure recovery, and mass flow are presented for five diffusers designed for maximum mass flow at Mach number 2.0.
Date: July 22, 1953
Creator: Nettles, J. C.
Partner: UNT Libraries Government Documents Department

Investigation of shock diffusers at Mach number 1.85 1: projecting single-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine design conditions for optimum performance of shock diffusers at Mach number 1.85 with a series of projecting single-shock cones with varying angles. Each cone was tested with a curved and a straight diffuser-inlet section. The effect of angle of attack was investigated for several configurations.
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Partner: UNT Libraries Government Documents Department

A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine

Description: Report presenting testing to determine which of three spinner-diffuser designs on an NACA cowling was the most effective in cooling a Pratt & Whitney R-2800 engine installation. The results of pressure-distribution studies in front of and behind each bank of cylinders are presented for a wide range of propeller-operating conditions.
Date: June 1944
Creator: Habel, Louis W. & Korycinski, Peter F.
Partner: UNT Libraries Government Documents Department

Use of constant diffuser Mach number as a control parameter for variable-geometry inlets at Mach numbers of 1.8 to 2.0

Description: Report presenting an analysis to determine the feasibility of using a constant diffuser Mach number to position a translating spike for optimum inlet performance. When the area at the diffuser Mach number sensing station is varied properly as the spike is translated, close to optimum inlet performance will be set by the control. Results regarding the inlet characteristics and performance with control are provided.
Date: November 4, 1957
Creator: Hearth, Donald P. & Anderson, Bernhard H.
Partner: UNT Libraries Government Documents Department

Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees.
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers 1: shock diffuser with triple-shock projecting cone

Description: Report presenting an investigation in the 20-inch supersonic tunnel at Mach number 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems. Results regarding diffuser performance with combustion, combustion with constant outlet-inlet area ratio, combustion with constant fuel flow, diffuser performance with combustion, and Mach number distribution at the diffuser outlet are provided.
Date: September 15, 1948
Creator: Connors, J. F. & Schroeder, A. H.
Partner: UNT Libraries Government Documents Department

Effects of diffuser and center-body length on performance of annular diffusers with constant-diameter outer walls and with vortex-generator flow controls

Description: Report presenting data for five diffusers tested with and without vortex-generator controls in order to determine the performance improvements attainable through the use of boundary-layer controls. Results regarding inlet conditions, axial inlet flow, and whirling inlet flow are provided.
Date: September 14, 1954
Creator: Wood, Charles C. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers 3: normal-shock diffuser

Description: Report presenting an experimental investigation on a ramjet in the 20-inch supersonic tunnel at a Mach number of 1.92 to determine the effects of combustion on the performance of a basic normal-shock diffuser. Total-pressure recovery with and without combustion was evaluated as a function of outlet-inlet area ratio and fuel flow. A rapid decrease in peak total-pressure recovery was obtained with increasing outlet-inlet area ratio.
Date: December 22, 1948
Creator: Schroeder, Albert H. & Connors, James F.
Partner: UNT Libraries Government Documents Department

Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0

Description: Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.
Date: August 12, 1952
Creator: Obery, L. J. & Krasnow, H. S.
Partner: UNT Libraries Government Documents Department