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Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 of Various Tip Controls on the Wing Panel of a 0.05-Scale Model of a Martin XASM-N-7 (Bullpup) Missile: TED No. NACA AD 3106
"An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the control effectiveness and hinge-moment characteristics of the Martin XASM-N-7 (Bullpup) missile. A half-scale wing panel was tested with a tip control having three different hinge-line locations. The tests were made over an angle-of-attack range from -10 to 10 degrees and a control-deflection range of -15 to 3 degrees" (p. 1).
Date:
1956~
Creator:
Driver, Cornelius
System:
The UNT Digital Library
Investigation of Suction Slot Shapes for Controlling a Turbulent Boundary Layer
Report presenting testing of several boundary-layer-control suction slots in a two-dimensional diffuser to develop design criteria and to evaluate the practical minimum total-pressure losses. The shape of the boundary layer behind the slot was found to depend only on the quantity of air removed provided the slot inert had rounded edges.
Date:
1956
Creator:
Pierpont, P. Kenneth
System:
The UNT Digital Library
Operational characteristics of RA-14 Avon turbojet engine
Report presenting a determination of the windmilling and altitude starting characteristics for the RA-14 Avon turbojet engine over a range of altitudes and flight Mach numbers. Successful ignition and acceleration to idle speed were obtained up to an altitude of 33,000 feet at all Mach numbers and at 45,000 feet for Mach numbers below 0.5 and above 1.0. Results regarding throttle bursts and wave-off-type acceleration and compressor-outlet bleed are also provided.
Date:
1956
Creator:
Sivo, Joseph N. & Jones, William L.
System:
The UNT Digital Library
Surge-Inception Study in a Two-Spool Turbojet Engine
Report discussing a study of compressor behavior leading to surge involving extensive instrumentation to obtain information about pressure at various points in the compressor. Information about where and under what conditions rotating stall occurred is given special attention.
Date:
1956
Creator:
Wallner, Lewis E.; Lubick, Robert J. & Saari, Martin J.
System:
The UNT Digital Library
Effect of an Adjustable Supersonic Inlet on the Performance Up to Mach Number 2.0 of a J34 Turbojet Engine
"A J34 turbojet engine was investigated at free-stream Mach numbers of 0.12 and 1.6 to 2.0 to determine the effect of supersonic inlet operation on engine performance. With the exception of ideal jet thrust, the use of generalized engine parameters correlated the engine data satisfactorily when the exit nozzle was choked. Large total-pressure distortions did not affect compressor efficiency" (p. 1).
Date:
January 4, 1956
Creator:
Beke, Andrew; Englert, Gerald & Beheim, Milton
System:
The UNT Digital Library
Effects of a J34 Turbojet Engine on Supersonic Diffuser Performance
Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.
Date:
January 4, 1956
Creator:
Beheim, Milton A. & Englert, Gerald W.
System:
The UNT Digital Library
An experimental investigation of a flat ram-jet engine on a helicopter rotor
Report presenting the propulsive and aerodynamic characteristics of a flat ramjet engine suitable for use on a helicopter rotor and compared with previous tests of an equivalent engine with a circular cross section. The results indicate that the flat engine has higher values of propulsive thrust plus power-off drag than the circular engine. The power-off and drag characteristics indicate that the flat engine has lift-drag ratios about 3 times those obtained with the circular engine.
Date:
January 4, 1956
Creator:
Powell, Robert D., Jr. & Shivers, James P.
System:
The UNT Digital Library
Investigation of a continuous normal-shock positioning control on the bypass of a supersonic inlet in combination with the J34 turbojet engine
Report presenting an investigation of a normal-shock positioning control which utilized the bypass of a supersonic inlet to set the required air flow for a J34 turbojet engines to Mach number 2.0 in the supersonic tunnel. Continuous control without oscillations was obtained by use of the pressure signal from the small static probe. Calculated response time generally agreed with measured values.
Date:
January 4, 1956
Creator:
Wilcox, Fred A.
System:
The UNT Digital Library
Static Lateral-Directional Stability Characteristics of Five Contemporary Airplane Models From Wind-Tunnel Tests at High Subsonic and Supersonic Speeds
Memorandum presenting the static lateral-directional stability characteristics of several airplane models recently investigated which cover many of the geometric arrangements of high-speed airplane components of current interest. The results are limited to the most pertinent aerodynamic phenomena contributing to the lateral-directional characteristics of each airplane type. Results for five different models are provided.
Date:
January 4, 1956
Creator:
Smith, Willard G. & Ball, Louis H.
System:
The UNT Digital Library
Static lateral-directional stability characteristics of five contemporary airplane models from wind-tunnel tests at high subsonic and supersonic speeds
Report presenting the static lateral-directional stability characteristics of several airplane models that cover many of the geometric arrangements of high-speed airplane components of current interest. The results are presented for a subsonic Mach number of 0.9 and for supersonic Mach numbers ranging from 1.2 to 1.9. Five different models are described and tested.
Date:
January 4, 1956
Creator:
Smith, Willard G. & Ball, Louis H.
System:
The UNT Digital Library
Static Shear Strength of 2117-T4 (A17S-T4) Aluminum-Alloy Rivets at Elevated Temperatures
Report presenting static single shear tests of 3/16-inch-diameter 2117-T4 (A17S-T4) aluminum-alloy rivets at elevated temperatures. The maximum temperature tested was 800 degrees Fahrenheit and the time at temperature prior to testing range from 1/2 hour to 720 hours.
Date:
January 4, 1956
Creator:
Dewalt, W. J. & Bogardus, K. O.
System:
The UNT Digital Library
Tank tests of a 1/8-size powered dynamic model of the Martin PBM-5 seaplane equipped with a single Edo hydro-ski : TED No. NACA AD3110
Report presenting an investigation of the hydrodynamic characteristics of a powered dynamic model of the Martin PBM-5 seaplane equipped with a single Edo hydro-ski. Various hydro-ski positions were investigated. Results regarding aerodynamic and hydrodynamic characteristics, including excess thrust, smooth-water landings, smooth-water take-offs, rough-water take-offs, and spray are provided.
Date:
January 6, 1956
Creator:
Coffee, Claude W., Jr.
System:
The UNT Digital Library
Analysis of a flight investigation at supersonic speeds of a simple homing system
From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."
Date:
January 10, 1956
Creator:
Gardiner, Robert A.; Gillis, Clarence L. & Graves, G. B., Jr.
System:
The UNT Digital Library
Effect of Throat Bleed on the Supersonic Performance of a Half-Conical Side-Inlet System
Memorandum presenting an experimental investigation conducted at Mach numbers 1.5, 1.8, and 2.0 to determine the effects of several throat boundary-layer bleed configurations on the performance of a 25 degree half-conical side-inlet system. The effects of several flush-slot configurations and a porous-surface bleed were determined over ranges of angle of attack and bleed-duct and main-duct mass flow.
Date:
January 10, 1956
Creator:
Sitt, Leonard E.; McKevitt, Frank X. & Smith, Albert B.
System:
The UNT Digital Library
A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-Wing-Body Combination Designed for High Performance
Report presenting an investigation of the effects of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance at a range of Mach numbers. Theoretical results of zero-lift wave drag for the wing-body combination agreed well with the experimental data. Results regarding the bodies, systematic series of wing-body combinations, -2 degree angle of incidence, M = 1.4 revised body, and transition are presented.
Date:
January 10, 1956
Creator:
Loving, Donald L.
System:
The UNT Digital Library
Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds
Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.
Date:
January 10, 1956
Creator:
McDearmon, Russell W. & Clark, Frank L.
System:
The UNT Digital Library
Flight Measurements of Section Efficiency, Thrust, and Power of a Supersonic-Type Propeller at Mach Numbers to 0.9
Report discussing testing on a supersonic-type propeller designed for a forward Mach number of 0.95, advance ratio of 2.2, and power coefficient of 0.26. Thrust distributions were found to be smooth and uniform over a range of Mach numbers, indicating efficient operation.
Date:
January 11, 1956
Creator:
Hammack, Jerome B. & O'Bryan, Thomas C.
System:
The UNT Digital Library
Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel
Report discussing tests of a model of a B-36J/RF-84F tip-coupled airplane to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain information about the dynamic stability characteristics. The variables studied were the skew angle of the fighter-bomber coupling, the fighter longitudinal position, the fighter and bomber loading, angle of sideslip, degrees of body freedom, and number of fighters. Flutter was primarily found to occur when the fighter roll frequency was near the natural chordwise-bending frequency of the bomber wing.
Date:
January 11, 1956
Creator:
Neely, Robert H.
System:
The UNT Digital Library
Initial inclination of the mixing boundary separating an exhausting supersonic jet from a supersonic ambient stream
Report presenting calculations of the initial inclination of the mixing boundary separating an exhausting supersonic jet from an external supersonic stream as a function of jet static-pressure ratio.
Date:
January 11, 1956
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Low-speed pressure-distribution investigation of a spoiler and a spoiler-slot-deflector on a 30 degree sweptback wing-fuselage model having an aspect ratio of 3, a taper ratio of 0.5, and NACA 65A004 airfoil section
Report presenting an investigation on a 30 degree sweptback wing-fuselage model in the 300 mph 7- by 10-foot tunnel to determine the effect of flap-type spoilers and spoiler-slot-deflectors on the chordwise and spanwise pressure distributions over the wing and controls. The results regarding the tabulated pressure, section force, and moment coefficients for six spanwise stations and curves of the variation of the total integrated force and moment coefficients with angle of attack for various control projections are provided.
Date:
January 11, 1956
Creator:
Hammond, Alexander D.
System:
The UNT Digital Library
Performance characteristics of cylindrical target-type thrust reversers
From tests on cylindrical target-type thrust reversers, it was found that the reverser frontal area, lip angle, end-plate angle, and end-plate depth had important effects on reverse-thrust performance. Frontal area, reverser depth, lip angle, and end-plate angele had important effects on the spacing required for unrestricted nozzle flow. For reverse-thrust ratios greater than 64 percent, the reversed flow attached to the 7 degree cowl in quiescent air. Swept-type cylindrical reversers were generally unstable. The thrust-modulation characteristics of a cylindrical target-type thrust reverser were found to be satisfactory.
Date:
January 11, 1956
Creator:
Steffen, Fred W. & McArdle, Jack G.
System:
The UNT Digital Library
Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination
Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.
Date:
January 11, 1956
Creator:
Platt, Robert J., Jr.
System:
The UNT Digital Library
Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines
For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date:
January 17, 1956
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Distribution of losses behind a compressor rotor as measured by a rotating rake
Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of low-speed momentum loss coefficient withe angle of attack, and variation of momentum-loss coefficient with Mach number are provided.
Date:
January 17, 1956
Creator:
Godwin, William R.
System:
The UNT Digital Library