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Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-Wedge Sections With the Maximum Thickness at 0.18 Chord
Report presenting a program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section in the hypersonic tunnel at Mach number 6.9. The wings varied at semiapex angle and were tested over a range of angles of attack and Reynolds numbers. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schlieren photographs, and surface film flow studies are presented.
Date:
October 20, 1954
Creator:
Bertram, Mitchel H. & McCauley, William D.
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Aerodynamic Characteristics of the Configuration Equipped With a Canard Control Surface at a Mach Number of 1.89
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a supersonic aircraft configuration equipped with a canard control surface at a Mach number of 1.89. The model had a 40 degree sweptback tapered wing with an aspect ratio of 4 and 10-percent-thick circular-arc sections normal to the quarter-chord line. Results regarding the pitching-moment characteristics, lift and longitudinal-force characteristics, longitudinal stability and control, and lateral stability characteristics are provided.
Date:
October 18, 1954
Creator:
Spearman, M. Leroy & Plazzo, Edward B.
System:
The UNT Digital Library
Free-flight measurements of the rolling effectiveness and operating characteristics of a bellows-actuated split-flap aileron on a 60 degree delta wing at Mach numbers between 0.8 and 1.8
Report presenting a free-flight investigation in a range of Mach numbers to determine the maximum deflection, zero-lift rolling effectiveness, and general operating characteristics of a bellows-actuated aileron control system energized by the pitot (impact) pressure. Testing of a system with a partial-span spit-flap aileron on a 60 degree delta wing showed that it is promising for obtaining lateral control at supersonic speeds. Results regarding aileron rolling effectiveness, aileron hinge moments, system time lag, estimation of aileron deflection, and aileron deflection control are provided.
Date:
October 18, 1954
Creator:
Schult, Eugene D.
System:
The UNT Digital Library
Effect of rotation of a NACA 1-series E-type cowling on the internal flow and force characteristics of the cowling at Mach numbers up to 0.84 and at an angle of attack of 0 degrees
Report presenting an investigation to determine the effect of rotation on the internal flow and force characteristics of an NACA 1-series E-type cowl, designed to operate with a four-blade single-rotation propeller. Results regarding internal-flow characteristics, force characteristics, and velocity distributions are provided.
Date:
October 27, 1954
Creator:
Sammonds, Robert I. & Reynolds, Robert M.
System:
The UNT Digital Library
Experimental Investigation at High Subsonic Speeds to Determine the Rolling-Stability Derivatives of Three Wing-Fuselage Configurations
Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.
Date:
October 27, 1954
Creator:
Sleeman, William C., Jr.
System:
The UNT Digital Library
Longitudinal Stability Characteristics in Accelerated Maneuvers at Subsonic and Transonic Speeds of the Douglas D-558-II Research Airplane Equipped with a Leading-Edge Wing Chord-Extension
Memorandum presenting an investigation of the Douglas D-558-II swept-wing research airplane with various modifications designed to alleviate swept-wing instability and pitch-up. In this study, the airplane was modified to include wing-chord extensions and was flight-tested.
Date:
October 27, 1954
Creator:
Fischel, Jack & Brunn, Cyril D.
System:
The UNT Digital Library
Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine
Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.
Date:
October 3, 1957
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date:
October 26, 1956
Creator:
Jorgensen, Leland H. & Katzen, Elliott D.
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.
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.
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
System:
The UNT Digital Library
Summary of Subsonic-Diffuser Data
Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.
Date:
October 12, 1956
Creator:
Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
System:
The UNT Digital Library
Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds
Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
Date:
October 12, 1954
Creator:
O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
System:
The UNT Digital Library
A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications
Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.
Date:
October 3, 1957
Creator:
Pierpont, P. Kenneth
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date:
October 7, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
System:
The UNT Digital Library
A Systematic Study of the Effects of Leading-Edge Chord-Extensions on the Low-Speed Longitudinal Stability Characteristics of Three 45 Degree Sweptback Wings
Memorandum presenting an investigation of a low-speed leading-edge chord extension in the 19-foot pressure tunnel. Chord-extensions of various geometric designs were tested on three 45 degree sweptback wings of aspect ratio 5 and taper ratio 0.28 incorporating different airfoil sections. The data indicated that leading-edge chord-extensions could be used to produce large reductions in the longitudinal instability of all three wings tested.
Date:
October 27, 1955
Creator:
Kelly, H. Neale
System:
The UNT Digital Library
Investigation of turbines suitable for use in a turbojet engine with high compressor ratio and low compressor-tip speed 5: experimental performance of two-stage turbine with downstream stator
An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.
Date:
October 21, 1951
Creator:
Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
System:
The UNT Digital Library
An Investigation of the Adaptation of a Transonic Slotted Tunnel to Supersonic Operation by Enclosing the Slots With Fairings
Memorandum presenting an experimental investigation of the adaptation of a transonic slotted tunnel to supersonic operation by enclosing the slots with fairings. The adaptation allows the extension of peak Mach number of the tunnel to be made at a reasonable cost in both time and effort, provided simplicity and ease of installation are taken into consideration during the design of the cover fairings. The nozzle is found to be sensitive to phenomena that will cause thickening of the boundary layer in the slot cover fairing.
Date:
October 6, 1955
Creator:
Matthews, Clarence W.
System:
The UNT Digital Library
Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385
From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date:
October 20, 1955
Creator:
Blanchard, Ulysse J. & Carter, Arthur W.
System:
The UNT Digital Library
Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing
Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date:
October 16, 1957
Creator:
Hanson, Perry W.
System:
The UNT Digital Library
A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor
Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.
Date:
October 16, 1957
Creator:
Cheatham, Donald C. & Mathews, Charles W.
System:
The UNT Digital Library
Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60
Report presenting an investigation to determine the effect of several seeker-nose configurations on the static longitudinal stability, canard control characteristics, and lift and drag at Mach number 1.60 of a canard-type ramjet missile with 70 degree delta canard control surfaces and 70 degree delta wings. The tests indicate that, for the most part, the configurations tested exhibited no significant difference in static longitudinal stability or horizontal-canard control effectiveness.
Date:
October 30, 1953
Creator:
Robins, A. Warner
System:
The UNT Digital Library
Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.
Date:
October 9, 1957
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library
Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles
Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date:
October 8, 1956
Creator:
King, Thomas J., Jr.
System:
The UNT Digital Library