Resource Type
Serial/Series Title
NACA Research Memorandums
192
Atomic Energy Commission Reports
99
Hanford Works Reports
22
NACA Technical Reports
22
HW (Series)
17
University of California Radiation Laboratory Reports
16
Oak Ridge National Laboratory Reports
15
BNL (Series)
12
Brookhaven National Laboratory Reports
12
Report (U.S. Atomic Energy Commission)
12
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383 Matching Results
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Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section: Transonic-bump method
Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.
Date:
August 23, 1950
Creator:
MacLeod, Richard G.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: A Pressure-Distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59
Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.
Date:
May 23, 1950
Creator:
Cooper, Morton & Spearman, M. Leroy
Object Type:
Report
System:
The UNT Digital Library
An Investigation of Several Supersonic Missile Configurations Directed Toward Minimizing Center-of-Pressure Travel
Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.
Date:
September 23, 1952
Creator:
Rainey, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7
Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.
Date:
September 23, 1952
Creator:
Chubb, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Effects of double-slotted flaps and leading-edge modifications on the low-speed characteristics of a large-scale 45 degrees swept-back wing with and without camber and twist
Report presenting an investigation of two large-scale, semispan, wing-fuselage models with the 0.25-chord line swept back 45 degrees to determine and compare the effects of partial-span, double-slotted flaps on the characteristics of a 45 degree sweptback wing with and without camber and twist. A secondary investigation was also conducted to determine the effects of various full-span, leading-edge modifications on the characteristics of the models with and without the flaps.
Date:
July 23, 1951
Creator:
James, Harry A. & Dew, Joseph K.
Object Type:
Report
System:
The UNT Digital Library
Large-scale flight measurements of zero-lift drag at Mach numbers from 0.8 to 1.6 of a wing-body combination having an unswept 4.5 percent thick wing with modified hexagonal sections
Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.
Date:
March 23, 1951
Creator:
Schult, Eugene D.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91
Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date:
September 23, 1952
Creator:
Cahill, Jones F. & Nuber, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail: longitudinal characteristics
Report presenting an investigation to determine the effect of an all-movable horizontal tail on the low-speed longitudinal characteristics of a triangular-wing airplane. The model consisted of a triangular wing of aspect ratio 2, a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and a thin, unswept, all-movable horizontal tail.
Date:
April 23, 1951
Creator:
Graham, David & Koenig, David G.
Object Type:
Report
System:
The UNT Digital Library
The properties of three cast polyester resins of Sierracin 212, 212A, and 250A
From Summary: "Physical properties of samples of three cast polyester resins known as Sierracin resins were investigated. Tests were made to determine specific gravity, index of refraction, Rockwell hardness, Tukon indentation hardness, effect of exposure to accelerated and outdoor weathering, Munsell color, resistance to accelerated service tests, crazing resistance under stress, flexural strength, Izod impact strength, and Taber abrasion resistance. Tables of the values obtained for these physical properties are included in the report."
Date:
April 23, 1951
Creator:
Kline, G. M.
Object Type:
Report
System:
The UNT Digital Library
Summary of Normal Accelerations, Gust Velocities, and Operating Practices, From April to August 1949 of a Twin-Engine Airplane in Commercial Transport Operations
Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.
Date:
August 23, 1950
Creator:
Steiner, Roy & McDougal, Robert L.
Object Type:
Report
System:
The UNT Digital Library
Tests of a small-scale NACA submerged inlet at transonic Mach numbers
Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.
Date:
February 23, 1950
Creator:
Rolls, L. Stewart & Rathert, George A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Low-speed investigation of the effects of nacelles on the longitudinal aerodynamic characteristics of a 60 degree sweptback delta-wing - fuselage combination with NACA 65A003 airfoil sections
Report presenting an investigation in the full-scale tunnel to determine the effects of symmetrically located wing nacelles on the low-speed aerodynamic characteristics of a 60 degree sweptback delta-wing-fuselage combination. The testing occurred with three spanwise nacelle locations with three chordwise positions at each spanwise station.
Date:
July 23, 1952
Creator:
Scallion, William I.
Object Type:
Report
System:
The UNT Digital Library
Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21
Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date:
June 23, 1952
Creator:
Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.
Object Type:
Report
System:
The UNT Digital Library
Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip
Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.
Date:
September 23, 1952
Creator:
Bennett, Charles V. & Boisseau, Peter C.
Object Type:
Report
System:
The UNT Digital Library
Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails
Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.
Date:
May 23, 1952
Creator:
Jaquet, Byron M.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements of the Lateral Stability and Control Characteristics of a High-Speed Fighter Airplane
Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.
Date:
September 23, 1952
Creator:
Crane, H. L.; Beckhardt, A. R. & Matheny, C. E.
Object Type:
Report
System:
The UNT Digital Library
Low speed stability characteristics of a complete model with a wing of W plan form
Report presenting an investigation of the low-speed static stability characteristics of a complete model equipped with a W wing. The lift-curve slope of the wing-fuselage combination was found to be in good agreement with that predicted by available wing-alone theory. Results regarding the longitudinal characteristics, wing-juncture modifications, and lateral and directional stability characteristics are provided.
Date:
April 23, 1952
Creator:
Polhamus, Edward C. & Becht, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration
Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.
Date:
June 23, 1952
Creator:
Leiss, Abraham
Object Type:
Report
System:
The UNT Digital Library
The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber
Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.
Date:
February 23, 1951
Creator:
Tinling, Bruce E. & Kolk, W. Richard
Object Type:
Report
System:
The UNT Digital Library
Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.
Date:
May 23, 1951
Creator:
Katzen, Elliott D. & Kaattari, George E.
Object Type:
Report
System:
The UNT Digital Library
Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system
The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date:
October 23, 1951
Creator:
Armstrong, John C.
Object Type:
Report
System:
The UNT Digital Library
Two-dimensional cascade investigation of the maximum exit tangential velocity component and other flow conditions at the exit of several turbine blade designs at supercritical pressure ratios
The nature of the flow at the exit of a row of turbine blades for the range of conditions represented by four different blade configurations was evaluated by the conservation-of-momentum principle using static-pressure surveys and by analysis of Schlieren photographs of the flow. It was found that for blades of the type investigated, the maximum exit tangential-velocity component is a function of the blade geometry only and can be accurately predicted by the method of characteristics. A maximum value of exit velocity coefficient is obtained at a pressure ratio immediately below that required for maximum blade loading followed by a sharp drop after maximum blade loading occurs.
Date:
August 23, 1951
Creator:
Hauser, Cavour H. & Plohr, Henry W.
Object Type:
Report
System:
The UNT Digital Library
Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight
Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date:
February 23, 1951
Creator:
Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination
Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.
Date:
May 23, 1951
Creator:
Pepper, William B., Jr. & Hoffman, Sherwood
Object Type:
Report
System:
The UNT Digital Library