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NACA Research Memorandums
5,157
NACA Technical Notes
4,107
NACA Technical Memorandums
1,438
NACA Technical Reports
1,423
NACA Wartime Reports
1,263
NACA Advanced Restricted Reports
533
NACA Memorandum Reports
338
NACA Advanced Confidential Reports
257
NACA Aircraft Circulars
223
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13,786 Matching Results
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Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date:
May 28, 1958
Creator:
Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.
Date:
June 18, 1957
Creator:
Morris, James F.
Object Type:
Report
System:
The UNT Digital Library
Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds
Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date:
November 30, 1955
Creator:
Keener, Earl R. & Jordan, Gareth H.
Object Type:
Report
System:
The UNT Digital Library
Evolution of the Helicopter
Report presenting an investigation of problems related to helicopters. Also included are the history of the evolution of the helicopter and a series of propeller experiments.
Date:
March 1923
Creator:
Balaban, Karl
Object Type:
Report
System:
The UNT Digital Library
Determination of Rate, Area, and Distribution of Impingement of Waterdrops on Various Airfoils From Trajectories Obtained on the Differential Analyzer
"The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders" (p. 1).
Date:
February 16, 1949
Creator:
Guibert, A. G.; Janssen, E. & Robbins, W. M.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of a New Type of Low-Drag Wing-Nacelle Combination
Report discusses the results of an experimental investigation of two low-drag wing-nacelle units suitable for use with pusher propellers. The benefits of adding a nacelle to the wing are detailed.
Date:
July 1942
Creator:
Allen, H. Julian & Frick, Charles W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01
Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date:
October 25, 1957
Creator:
Morris, Owen G. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Stability and Control Characteristics at Low Speed of a 1/10-Scale Model of MX-1554A Design
Report discussing an investigation of the low-speed stability and control characteristics of a model of the proposed MX-1554A design with a triangular wing and triangular stabilizing surfaces. It also includes the effect of wing incidence, slotted flaps, wing and tail height, external tanks and speed brakes, ground board, spoilers, tip ailerons, flaps, differential tail deflection, and an unswept wing on stability, control, aerodynamic, longitudinal, and lateral characteristics.
Date:
1953
Creator:
Lockwood, Vernard E. & Solomon, Martin
Object Type:
Report
System:
The UNT Digital Library
Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date:
October 16, 1956
Creator:
Robinson, Ross B. & Foster, Gerald V.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2
Report discussing testing of the effects of aeroelasticity on the rolling effectiveness on a model of a McDonnell F-101A airplane wing. The aeroelastic losses varied based on the Mach number and altitude.
Date:
September 2, 1955
Creator:
English, Roland D.
Object Type:
Report
System:
The UNT Digital Library
Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design
Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.
Date:
November 9, 1953
Creator:
Lockwood, Vernard E. & Solomon, Martin
Object Type:
Report
System:
The UNT Digital Library
Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design
Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date:
October 29, 1953
Creator:
Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
Object Type:
Report
System:
The UNT Digital Library
Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle
Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
Date:
January 7, 1954
Creator:
Solomon, Martin
Object Type:
Report
System:
The UNT Digital Library
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53
Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coefficients, neutral points, directional stability, and positive effective dihedral is provided.
Date:
November 30, 1956
Creator:
Turner, Kenneth L. & Fournier, Roger H.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane
Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.
Date:
November 14, 1957
Creator:
Paulson, John W.
Object Type:
Report
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.
Date:
January 13, 1958
Creator:
Healy, Frederick M.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01
"A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger" (p. 1).
Date:
January 15, 1957
Creator:
Kouyoumjian, Walter L.
Object Type:
Report
System:
The UNT Digital Library
Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds
Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
Date:
August 23, 1955
Creator:
Neely, Robert H. & Griner, Roland F.
Object Type:
Report
System:
The UNT Digital Library
Transonic Aerodynamic and Trim Characteristics of 1/15-Scale Models of the Convair MX-1964 Airplane With Indented Fuselage
Report presenting an investigation of two scale models of the MX-1964 airplane with indented fuselage conducted in the transonic tunnel. One model had a plane delta wing with full-span elevons and the other had a cambered delta wing with partial-span elevons. Results regarding the aerodynamic characteristics and effect of elevon deflection are provided.
Date:
1953
Creator:
Allis, Arthur E.; Swihart, John M. & Foss, Willard E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date:
August 1, 1958
Creator:
McKinney, Marion O. & Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date:
July 21, 1958
Creator:
Heath, Atwood R., Jr. & Igoe, Ann W.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats
Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparisons with flight data are provided.
Date:
July 5, 1957
Creator:
James, Harry A. & Maki, Ralph L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25
Aerodynamic characteristics of rectangular platform, all-movable controls combined with slender body of revolution at Mach 3 to 6.25. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
Date:
December 28, 1955
Creator:
Wong, Thomas J. & Gloria, Hermilo R.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
Date:
January 19, 1953
Creator:
Karp, Irving M.
Object Type:
Report
System:
The UNT Digital Library