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Performance of twin-duct variable-geometry side inlets at mach numbers of 1.5 to 2.0

Description: Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.
Date: January 21, 1957
Creator: Yeager, Richard A.; Beheim, Milton A. & Klann, John L.

Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Description: A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases. A high-temperature wind tunnel that allowed calibration of the probe at temperatures up to 2000 deg R and. Mach numbers up to 0.8 is described. Agreement to better than 30 deg R between pneumatic probe indication and the indication of a rake of radiation shielded thermocouples indicates that extrapolation of the calibration to higher temperatures is possible with fair accuracy.
Date: May 21, 1952
Creator: Scadron, Marvin D.

Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, the location of the maximum diameter is not arbitrary but is determined from the ratio of base diameter to maximum diameter.
Date: August 21, 1951
Creator: Adams, Mac C.

Wind-tunnel investigation of the effect of spin on the aerodynamic characteristics of a 60-millimeter T-24 mortar shell with several tail-fin configurations

Description: Report discussing an investigation to determine the effect of spin on the aerodynamic characteristics of the Army Ordnance Corps 60-millimeter T-24 mortar shell with several tail-fin configurations. Tests were performed at several airspeeds, speeds of rotation, and angles of attack. Under all test conditions, the models were statistically stable and the yawing moment increased with speed of rotation at higher angles of attack.
Date: March 21, 1957
Creator: Kemp, William B., Jr. & Hayes, William C., Jr.

Altitude starting tests of a small solid propellant rocket

Description: From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date: June 21, 1957
Creator: Sloop, John L. & Krawczoner, Eugene M.

Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations

Description: Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date: July 21, 1958
Creator: Penland, Jim A. & Armstrong, William O.

Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets

Description: The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results. In addition, the results indicated that bleeding around the periphery ahead of the compressor-face station improved pressure recovery and compressor-face distortion, especially at angle of attack.
Date: October 21, 1957
Creator: Anderson, B. H.; Dryer, M. & Hearth, D. P.

An investigation of the dynamic and static stability characteristics of a group of specialized store configurations at transonic speeds

Description: Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date: August 21, 1953
Creator: Henry, Beverly Z. & Braden, John A.

Internal flow and burning characteristics of 16-inch ram jet operating in a free jet at Mach numbers of 1.35 and 1.73

Description: The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-shock diffuser are presented. Also evaluated is the variation with operating condition of the velocity distribution at the combustion-chamber inlet. A comparison with connected-pipe data is included. Burner performance with a corrugated gutter-grid flame holder is discussed. It is shown that the total-pressure drop across the combustion chamber can be predicted with reasonable accuracy from the computed flame holder and combustion momentum pressure losses.
Date: May 21, 1951
Creator: Perchonok, Eugene & Farley, John M

Performance of three high-recovery-factor thermocouple probes for room-temperature operation

Description: From Summary: "Thermocouple probes have been designed to measure with small error the total temperature of gas moving at high velocities. Two major designed are presented: one is applicable to the construction of rakes and the other, of which there are two variations, can be used where exceptional accuracy is desired. The probes were calibrated in two jets; one jet exhausted into the atmosphere and the other into a pressure-controlled receiver."
Date: December 21, 1950
Creator: Scadron, Marvin D.; Gettelman, Clarence C. & Pack, George J.

Drag investigation of some fin configurations for booster rockets at Mach numbers between 0.5 and 1.4

Description: Report discussing testing to obtain data on booster drag estimates and to investigate the drag of various booster fin configurations. Several tie-rod-braced fin assemblies were investigated with various types and arrangement of tie rods as well as a cantilever fin assembly. The cantilever fin assembly was found to have roughly the same drag coefficients as the most efficient tie-rod-braced assembly.
Date: November 21, 1950
Creator: McFall, John C., Jr.

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Description: Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Date: July 21, 1950
Creator: Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.

Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F

Description: Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.
Date: September 21, 1950
Creator: Kinney, George R. & Sloop, John L.

Altitude-wind-tunnel investigation of turbine performance in J47 turbojet engine

Description: From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date: September 21, 1950
Creator: Thorman, H. Carl & McAulay, John E.

Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section

Description: Report discusses the result of tests determining the longitudinal-stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, a thickened tip section, and a twisted and cambered shape. The wing was tested with a fuselage and various devices for altering stall and spanwise boundary-layer flow. Measurements of force, pressure-distribution, and span load distribution are described.
Date: November 21, 1950
Creator: Weiberg, James A. & Carel, Hubert C.

Preliminary flight investigation of the maneuvering accelerations and buffet boundary of a 35 degree swept-wing airplane at high altitude and transonic speeds

Description: Report presenting the results of a series of exploratory flights on a 35 degree swept-wing airplane up to Mach number 1.09 to show the effects of compressibility on imposing maneuverability limits. Results regarding the maneuvering accelerations and buffet boundary are provided.
Date: February 21, 1951
Creator: Rathert, George A., Jr.; Ziff, Howard L. & Cooper, George E.

Theoretical and experimental investigation of additive drag

Description: The significance of additive drag is discussed and equations for determining its approximate value are derived. Charts are presented giving values of additive drag for open-nose inlets and for annular-nose inlets with conical flow at the inlet. The effects of variable inlet total-pressure recovery and static pressures on the center body are investigated, and an analytical method of predicting the variation of pressure on the center body with mass-flow ratio is given. Experimental values of additive drag are compared with values predicted by the methods.
Date: May 21, 1951
Creator: Sibulkin, Merwin