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NACA Research Memorandums
107
Atomic Energy Commission Reports
33
Oak Ridge National Laboratory Reports
16
Hanford Works Reports
15
HW (Series)
13
NACA Technical Reports
12
University of California Radiation Laboratory Reports
12
Battelle Memorial Institute Reports
6
CF (Series)
6
ORNL (Series)
6
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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.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls
Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree fins and trailing-edge flaps, and body with 10 degree flare and all-movable controls.
Date:
August 4, 1958
Creator:
Robinson, Ross B. & Bernot, Peter T.
Object Type:
Report
System:
The UNT Digital Library
Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets
Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.
Date:
November 4, 1955
Creator:
Letko, William & Williams, James L.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal Aerodynamic Characteristics of Various Configurations of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
Report presenting an investigation of a model of the Republic F-105 airplane to determine the static longitudinal aerodynamic characteristics of a revised configuration. The revisions included a lengthened fuselage, a relocated canopy, a contoured fuselage afterbody, a ventral fin, and an enlarged vertical tail. Results regarding the effect of stores, effect of dive-brake flaps, effect of forebody modifications, gun blisters, and duct air bleed, and a comparison of the modified model with the original are provided.
Date:
May 4, 1956
Creator:
Foster, Gerald V.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation of Cyclic De-Icing of an Airfoil Using an External Electric Heater
"An investigation was conducted in the NACA Lewis icing research tunnel to determine the characteristics and requirements of cyclic deicing of a 65,2-216 airfoil by use of an external electric heater. The present investigation was limited to an airspeed of 175 miles per hour. Data are presented to show the effects of variations in heat-on and heat-off periods, ambient air temperature, liquid-water content, angle of attack, and. heating distribution on the requirements for cyclic deicing" (p. 1).
Date:
February 4, 1952
Creator:
Lewis, James P. & Bowden, Dean T.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body
"An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body" (p. 1).
Date:
May 4, 1950
Creator:
Conner, D. William & Guy, Lawrence D.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Flight Measurements of the Total-Pressure Recovery of a Split-Wing Ram-Jet Inlet at Mach Numbers from 1.4 to 3.16
"Flight tests were made to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a Mach number range from 1.4 to 3.16. Total-pressure-recovery measurements at the diffuser exist station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range. Comparisons of average total-pressure recovery with the theoretical total-pressure recovery showed good agreement" (p. 1).
Date:
March 4, 1954
Creator:
Hinners, Arthur H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine
"Characteristic exhaust velocity was measured for a small range of mixture ratios with four different injectors. Performances of parallel-sheet, like-on-like, and triplet injectors were about the same, but a parallel-jet injector had a much lower performance. Performance values for ammonia-oxygen were slightly lower than for heptane-oxygen" (p. 1).
Date:
September 4, 1958
Creator:
Priem, Richard J. & Clark, Bruce J.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Several Jet-Engine Air-Inlet Configurations on the Low-Speed Static Lateral Stability Characteristics of a 1/6- Scale of the MX-1764 Airplane
Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally had only small effects on the lateral stability.
Date:
March 4, 1954
Creator:
Croom, Delwin R.
Object Type:
Report
System:
The UNT Digital Library
Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All-Movable Control
"The static aeroelastic divergence characteristics of a delta-plan-form model of the canard control surface of a proposed air-to-ground missile have been studied both analytically and experimentally in the Mach number range from 0.6 to 3.0. The experiments indicated that divergence occurred at a nearly constant value of dynamic pressure at Mach numbers up to 1.2. At higher Mach numbers somewhat higher values of dynamic pressure were required to produce divergence" (p. 1).
Date:
August 4, 1958
Creator:
Rainey, A. Gerald; Hanson, Perry W. & Martin, Dennis J.
Object Type:
Report
System:
The UNT Digital Library
Use of Constant Diffuser Mach Number as a Control Parameter for Variable-Geometry Inlets at Mach Numbers of 1.8 to 2.0
Memorandum presenting an analysis to determine the feasibility of using a constant diffuser Mach number to position a translating spike for optimum inlet performance. A control system incorporating this concept was investigated on a blunt lip, translating-spike inlet at flight Mach numbers of 1.8 to 2.0 and angles of attack up to 6 degrees. Results regarding inlet characteristics and performance with control are provided.
Date:
November 4, 1957
Creator:
Hearth, Donald P. & Anderson, Bernhard H.
Object Type:
Report
System:
The UNT Digital Library
The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.
Date:
April 4, 1950
Creator:
Matthews, Howard F.
Object Type:
Report
System:
The UNT Digital Library
Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds
Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag research models equipped wing wing tanks at a range of Mach numbers. The tanks, which were slender bodies of revolution, were mounted on 34 degrees sweptback, nontapered wings of 2.7 aspect ratio. Results regarding drag and trim change are provided.
Date:
April 4, 1950
Creator:
Welsh, Clement J. & Morrow, John D.
Object Type:
Report
System:
The UNT Digital Library
A description of the design of highly swept propeller blades
"A description of the two swept propellers investigated in the Langley 8-foot high-speed tunnel is presented, together with the discussions of the numerous assumptions and analyses on which the designs of these propellers are based. The blades are swept considerably along the entire blade radius and, in order to allow for reductions in the maximum stresses, are swept forward inboard and backward outboard. The blades have been designed on the basis of the blade-element method primarily to have subcritical efficiencies at the highest possible forward speed. The designs have been controlled primarily by the stresses in the blades" (p. 1).
Date:
May 4, 1950
Creator:
Whitcomb, Richard T.
Object Type:
Report
System:
The UNT Digital Library
Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area
Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with design rules are provided.
Date:
September 4, 1958
Creator:
Montgomery, John C. & Yasaki, Paul T.
Object Type:
Report
System:
The UNT Digital Library
Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4
Report presenting an experimental investigation of the downwash and sidewash flow angles in a transverse plane behind a cruciform-wing and body combination. The wing-body combination had a cruciform arrangement of two identical triangular wings of aspect ratio 2.31 corresponding to a leading-edge sweep angle of 60 degrees placed on a body of fineness ratio of 16. The investigation was conducted at a specified Mach and Reynolds number and a range of angles of bank and attack.
Date:
April 4, 1951
Creator:
Wetzel, Benton E. & Pfyl, Frank A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of centrifugal compressor operated as a centripetal refrigeration turbine
Report presenting testing of a centrifugal compressor from a production-type turbojet engine, which was successfully operated as a centripetal refrigeration turbine over a range of rotor speed, inlet pressure, and pressure ratio for full admission. The performance results indicated that partial admission was found to be the most efficient method of turbine control, but throttling at the turbine inlet was easy to apply. When nozzles are used, they should have erosion-resistant surfaces to minimize erosion effects.
Date:
December 4, 1950
Creator:
Rebeske, John J., Jr.; Parisen, Richard B. & Schum, Harold J.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy
"Pressure-distribution measurements and load-coefficient data at low speeds obtained in flight for a conventional front and rear sliding canopy are presented. The load-coefficient data indicate that the highest net aerodynamic load for the front canopy was in the exploding direction and occurred with the front and rear canopies closed. The highest net load for the rear canopy was in the crushing direction with the front canopy open and the rear canopy closed" (p. 1).
Date:
April 4, 1950
Creator:
Huston, Wilber B. & Skopinski, T. H.
Object Type:
Report
System:
The UNT Digital Library
A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques
Report presenting a comparison of the high-speed aerodynamic characteristics of a family of four wing-fuselage configurations with four different degrees of sweepback as determined from transonic-bump model tests in the 7- by 10-foot tunnel, sting-supported model tests in the 8-foot tunnel, and the 7-foot by 10-foot tunnel.
Date:
October 4, 1950
Creator:
Donlan, Charles J.; Myers, Boyd C., II & Mattson, Axel T.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Blade-Section Camber on the Static Characteristics of Three NACA Propellers
Report discussing static testing on 3 NACA two-blade propellers with design lift coefficients of 0, 0.3, and 0.5. Information about the effect of camber on the static-thrust figure of merit, the effect of camber on the stall-flutter speed, thrust coefficient, and blade flutter is provided.
Date:
April 4, 1952
Creator:
Wood, John H. & Swihart, John M.
Object Type:
Report
System:
The UNT Digital Library
Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a tip-to-tip bomber-fighter coupled airplane configuration
Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with freedom in roll and pitch, and with freedom in roll, pitch, and yaw are provided.
Date:
April 4, 1951
Creator:
Bennett, Charles V. & Cadman, Robert B.
Object Type:
Report
System:
The UNT Digital Library
Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination
Report presenting measurements made at a Mach number of 0.25 of the aerodynamic characteristics of a wing with an aspect ratio of 3 combined separately with three geometrically similar bodies of revolution with the same fineness ratio but differing sizes. Results regarding wings, bodies of revolution, wing in the presence of the bodies, wing combined with the bodies of revolution, and effect of wing incidence changes are provided.
Date:
October 4, 1951
Creator:
Hopkins, Edward J. & Carel, Hubert C.
Object Type:
Report
System:
The UNT Digital Library
Nonlifting Wing-Body Combinations With Certain Geometric Restraints Having Minimum Wave Drag at Low Supersonic Speeds
"Several variational problems involving optimum wing and body combinations having minimum wave drag for different kinds of geometrical restraints are analyzed. Particular attention is paid to the effect on the wave drag of shortening the fuselage and, for slender axially symmetric bodies, the effect of fixing the fuselage diameter at several points or even of fixing whole portions of its shape" (p. 113).
Date:
August 4, 1955
Creator:
Lomax, Harvard
Object Type:
Report
System:
The UNT Digital Library
Theoretical analysis of incompressible flow through a radial-inlet centrifugal impeller at various weight flows
A method for the solution of the incompressible nonviscous flow through a centrifugal impeller, including the inlet region, is presented. Several numerical solutions are obtained for four weight flows through an impeller at one operating speed. These solutions are refined in the leading-edge region. The results are presented in a series of figures showing streamlines and relative velocity contours. A comparison is made with the results obtained by using a rapid approximate method of analysis.
Date:
March 4, 1955
Creator:
Kramer, James J.; Prian, Vasily D. & Wu, Chung-Hua
Object Type:
Report
System:
The UNT Digital Library