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Investigation of the Pressure-Loss Characteristics of the Westinghouse X24-C-2 Inlet Screen, TED No. NACA 0447

Description: At the request of the Bureau of Aeronautics, Navy Department, investigations of the static-pressure losses and total-head distributions of the Westinghouse X24-C-2 inlet screen were made in the induction aerodynamics laboratory at Langley. The screen was investigated in two configurations, both before and after rounding the leading edges of the vanes. Investigations were conducted through air flows up to about pounds per second.
Date: December 2, 1946
Creator: Lankford, John L.
Partner: UNT Libraries Government Documents Department

Flight determination of drag of normal-shock nose inlets with various cowling profiles at Mach numbers from 0.9 to 1.5

Description: External-drag data are presented for normal-shock nose inlets with NACA 1-series, parabolic, and conic cowling profiles. The tests were made at an angle of attack of 0 degrees by using rocket-propelled models in free flight at Mach numbers from 0.9 to 1.5. The Reynolds number based on body maximum diameter varied from 2.5 x 10 sup 6 to 5.5 x 10 sup 6. At maximum flow rate, the inlet models had about the same external drag at a Mach number of approximately 1.1, but at higher Mach numbers the sharp-lip conic cowling had the least drag. Blunting or beveling the lip of the conic cowling while keeping the fineness ratio constant resulted in drag coefficients slightly higher than for the sharp-lip conic cowling at maximum flow rate. At a mass-flow ratio of about 0.8, the conic cowlings with sharp, blunt, or beveled lips and the parabolic cowling all gave about the same drag. The higher drag of the NACA 1-49-300 cowling, compared with the blunt-lip conic cowling, is associated with the greater fullness back of the inlet.
Date: September 8, 1953
Creator: Sears, R. I.; Merlet, C. F. & Putland, L. W.
Partner: UNT Libraries Government Documents Department

Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0

Description: Report presenting free-flight testing of conical-shock nose inlet models with cowls of fineness ratio 3 with five different profiles. Three of the profiles were mostly conic with different lip shapes, one was parabolic, and one was NACA 1-series. Results regarding the basic data, effect of cone position, comparison of profile shapes, and effect of mass-flow ratio are provided.
Date: September 10, 1954
Creator: Merlet, Charles F. & Putland, Leonard W.
Partner: UNT Libraries Government Documents Department

A flight comparison of a submerged inlet and a scoop inlet at transonic speeds

Description: Report presenting flight tests conducted on two different inlet configurations, a submerged divergent-wall inlet and scoop inlet, to determine their characteristics when installed on a YF-93 airplane. Measurements were made of the pressure-recovery characteristics of the inlets and overall airplane drag for each configuration. Results regarding the induction-system efficiency, airplane drag, and a relative comparison of the inlet installations are provided.
Date: March 19, 1953
Creator: Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department

Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1

Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct.
Date: December 28, 1956
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of a conical spike inlet in combination with a vertical-wedge auxiliary inlet at Mach number 1.9

Description: Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge auxiliary scoop are presented for a free-stream Mach number of 1.9 at zero angle of attack. The auxiliary scoop provided 17 percent additional air flow with a drop in critical pressure recovery from 0.86 to 0.81. However, in terms of inlet-engine matching, the pressure recovery of the undersized spike inlet operating at a specified corrected air flow increased with the scoop open, for example, from 0.69 to 0.81.
Date: September 27, 1955
Creator: Beke, Andrew; Allen, John L. & Williams, Thomas
Partner: UNT Libraries Government Documents Department

Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0

Description: Inserting a splitter plate in the subsonic diffuser caused a pressure-recovery loss of about 1 percent for an inlet with a long nearly constant-area throat section. The loss was due to the increased surface area. Another inlet, which had a comparatively rapid area increase immediately after the throat, experienced pressure-recovery losses of 5 and 6 percent at Mach numbers of 1.8 and 2.0, respectively, and about 1 percent at Mach 1.5.
Date: December 19, 1955
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department

Effect of circumferential location on angle of attack performance of twin half-conical scoop-type inlets mounted symmetrically on the RM-10 body of revolution

Description: Report presenting an investigation to determine the effect of circumstantial inlet location on the performance of twin half-conical scoop-type inlets with and without boundary-layer removal at several Mach numbers and angles of attack. For positive angles of attack, higher pressure recovery performance was obtained with the inlets mounted on lower fuselage quadrants than on upper quadrants.
Date: September 9, 1953
Creator: Valerino, Alfred S.; Pennington, Donald B. & Vargo, Donald J.
Partner: UNT Libraries Government Documents Department

Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 1: two-dimensional compression-ramp inlets with semicircular cowls

Description: Report presenting an experimental investigation to determine the performance of twin-scoop side inlets located on the fuselage of a proposed aircraft in a region of large boundary-layer thickness. Inlet configurations with subsonic and supersonic cowlings which utilized two-dimensional compression ramps and ram-type scoops for boundary-layer-removal systems were investigated at several Mach number ranges. Results regarding supersonic Mach number range, angle of attack, subsonic Mach number, and static conditions are provided.
Date: July 16, 1952
Creator: Valerino, Alfred S.
Partner: UNT Libraries Government Documents Department

Effect of uneven air-flow distribution to the twin inlets of an axial-flow turbojet engine

Description: Report presenting a brief investigation conducted to determine the effects of a 60-40 air flow distribution to the twin inlet ducts of an axial-flow turbojet engine. Data were obtained over a range of exhaust gas temperatures at several altitudes at Mach number 0.64. Results regarding the effect on pressure and temperature patterns, compressor performance, effect on combustor and turbine performance, engine pumping characteristics, and operational characteristics are provided.
Date: January 26, 1953
Creator: Wallner, Lewis E.; Conrad, E. William & Prince, William R.
Partner: UNT Libraries Government Documents Department

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Description: Report presenting an investigation of an all-internal conical compression inlet with annular bleed at the throat at Mach number 5.0 and zero angle of attack. Results regarding the performance of the diffuser alone, a Pitot-pressure survey of the flow leaving the diffuser, total-pressure distribution, and inlet efficiencies are provided.
Date: August 6, 1958
Creator: Stitt, Leonard E. & Obery, Leonard J.
Partner: UNT Libraries Government Documents Department

Performance of external-compression bump inlet at Mach numbers of 1.5 and 2.0

Description: Report presenting an experimental investigation of a scale model of the forebody of a proposed supersonic fighter to determine the internal performance and configuration drag of various twin-side inlets. External-compression ramp and bump inlets with various types and combinations of boundary-layer bleed were tested. Results regarding performance charts and flow characteristics are provided.
Date: April 24, 1957
Creator: Simon, Paul C.; Brown, Dennis W. & Huff, Ronald G.
Partner: UNT Libraries Government Documents Department

Investigation of mass-flow and pressure recovery characteristics of several underslung scoop-type inlets at free-stream Mach numbers of 2.0, 1.8, 1.5, and 0.66

Description: Report presenting testing of several underslung scoop-type inlets mounted on a body of revolution at several Mach numbers through a range of angles of attack. Geometric differences between inlets included ramp angle, frontal area, splitter-plate height, and aspect ratio. Results regarding inlet stability, peak pressure recoveries, and total-pressure distortions are provided.
Date: March 13, 1957
Creator: Valerino, Alfred S. & Zappa, Robert F.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85

Description: Report presenting an experimental investigation of the performance capabilities of an asymmetric swept nose inlet of circular projection in the supersonic wind tunnel at a Mach number of 3.85. The aysmmetric inlet was evaluated in terms of its pressure recovery and mass-flow characteristics for angles of attack up to 9 degrees. Results regarding diffuser performance, supercritical flow patterns, oblique shocks, subcritical stability ranges, and Mach number profiles are provided.
Date: October 11, 1954
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department

A low-speed investigation of a fuselage-side air inlet for use at transonic flight speeds

Description: Low-speed pressure-recovery and surface-pressure measurements for a twin fuselage-side air-inlet arrangement intended for use at transonic speeds are presented. The model was developed by adding a canopy and nose-wheel fairing to basic transonic annular inlet studied in TN 2685. The results indicate shape requirements of fuselage nose, canopy, and nose-wheel fairing for maintaining substream surface velocities everywhere ahead of entrance.
Date: April 1952
Creator: Nichols, Mark R. & Goral, Edwin B.
Partner: UNT Libraries Government Documents Department

A low-speed investigation of an annular transonic air inlet

Description: Low-speed wind-tunnel tests were conducted as preliminary steps in the study of fuselage-air-inlet arrangements believed suitable for use at transonic speeds. The forward part of the model consisted of an NACA 1-85-050 cowling located at the base of the long protruding fuselage nose designed to maintain substream surface velocities everywhere ahead of the entrance and thereby to avoid or minimize adverse boundary-layer-shock interaction effects up to low supersonic speeds. Pressure-recovery and surface-pressure measurements are presented for the model with three fuselage nose shapes for ranges of angle of attack and inlet-velocity ratio useful for high-speed flight.
Date: April 1952
Creator: Nichols, Mark R. & Rinkoski, Donald W.
Partner: UNT Libraries Government Documents Department

Fuselage side inlets : a study of some factors affecting their performance and a comparison with nose inlets

Description: Report presenting basic principles affecting the performance of side-inlet air-induction systems as well as an examination of the performance of several fuselage side inlets and a comparison with nose inlets. Methods for improving the performance of both types of inlets are reviewed.
Date: April 2, 1956
Creator: Mossman, Emmet A.; Pfyl, Frank A. & Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department

Performance of a double-cone inlet with and without a shroud at below-design Mach numbers

Description: Report presenting values of zero angle-of-attack performance of a double-cone inlet with and without a shroud through a range of mass-flow ratios and Mach numbers. Maximum propulsive thrust was computed to be higher with the shrouded inlet at all supersonic Mach numbers tested. Results regarding internal diffuser performance, drag, and engine performance are provided.
Date: March 3, 1955
Creator: Pennington, Donald; Rabb, Leonard & Simpkinson, Scott H.
Partner: UNT Libraries Government Documents Department

Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Description: Report presenting an investigation of air-launched ram jets using models with double-cone inlets with a design free-stream Mach number of 2.4. Drag data are presented in the form of cowl pressure drag, additive drag, internal drag, base drag, and total drag. Mass-flow ratios and ram-jet total-temperature ratios are also provided.
Date: October 25, 1954
Creator: Jones, Merle L.; Rabb, Leonard & Simpkins, Scott H.
Partner: UNT Libraries Government Documents Department

An investigation of three transonic fuselage air inlets at Mach numbers from 0.4 to 0.94 and at a Mach number of 1.19

Description: Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.
Date: November 7, 1950
Creator: Pendley, Robert E.; Robinson, Harold L. & Williams, Claude V.
Partner: UNT Libraries Government Documents Department

An experimental investigation of the air-flow of a scoop-type normal-shock inlet

Description: Report presenting an experimental investigation of the airflow stability of scoop-type normal-shock inlets located on the fuselage of a model of an interceptor or fighter-type airplane. Pressure recovery and amplitude of pressure pulsations were measured for several Mach numbers and mass-flow ratios.
Date: April 28, 1955
Creator: Mossman, Emmet A.; Lazzeroni, Frank A. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Description: Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.
Date: June 2, 1948
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department

The effect of the propeller slipstream on the characteristics of submerged inlets

Description: Report presenting a wind-tunnel investigation to determine the effect of propeller operation on the characteristics of submerged inlets. The tests were performed with a model of a hypothetical fighter airplane powered by a turbine-propeller unit. The propeller had eight blades with thin airfoil shanks and dual rotation and the submerged inlets were placed in the fuselage behind the propeller and forward of the wing.
Date: September 9, 1949
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department