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Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance
From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry."
Date:
September 11, 1956
Creator:
Allen, H. Julian
System:
The UNT Digital Library
Problems of performance and heating of hypersonic vehicles
Report presenting a comparison of three hypervelocity vehicles: a ballistic rocket, a skip rocket, and a rocket glider. Range efficiency, automatic heating, and problems of glide rockets are explored.
Date:
March 5, 1956
Creator:
Allen, H. Julian & Neice, Stanford E.
System:
The UNT Digital Library
Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1
Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct.
Date:
December 28, 1956
Creator:
Allen, John L.
System:
The UNT Digital Library
Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1
Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date:
December 28, 1956
Creator:
Allen, John L.
System:
The UNT Digital Library
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.
Date:
August 3, 1956
Creator:
Allen, John L. & Piercy, Thomas G.
System:
The UNT Digital Library
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Report presenting testing of the performance of a ventrally mounted inlet having a variable-angle vertical-wedge compression surface determined at several Mach numbers for angles of attack, angles of yaw, and wedge angle. A solid wedge and wedges with two different porosities were tested. Results regarding the inlet flow-field survey, comparison of inlet configurations, performance of the inlet, effect of free-stream Mach number at angle of attack of 2 degrees, effect of angles of attack and yaw, diffuser total-pressure distortion, fuselage boundary-layer-removal scoop, and effective thrust comparison are provided.
Date:
August 3, 1956
Creator:
Allen, John L. & Piercy, Thomas G.
System:
The UNT Digital Library
Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with area suction boundary-layer control on the flaps
Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.
Date:
February 3, 1956
Creator:
Anderson, Seth B. & Quigley, Hervey C.
System:
The UNT Digital Library
Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with blowing-type boundary-layer control in the trailing-edge flaps
Report presenting tests to determine the flight characteristics of an F-86 airplane equipped with a blowing-type boundary-layer-control installation on the trailing-edge flaps. The effectiveness of the flap was determined in conjunction with slatted leading edges and an inflatable rubber boot on the leading edge. Measurements were made of lift, drag, flow requirements, and computations for take-off, climb, and landing.
Date:
October 25, 1956
Creator:
Anderson, Seth B.; Quigley, Hervey C. & Innis, Robert C.
System:
The UNT Digital Library
Longitudinal stability characteristics of the Convair YF-102 airplane determined from flight tests
Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.
Date:
December 13, 1956
Creator:
Andrews, William H.; Sisk, Thomas R. & Darville, Robert W.
System:
The UNT Digital Library
Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds
Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.
Date:
January 17, 1956
Creator:
Arabian, Donald D.
System:
The UNT Digital Library
Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail
Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date:
June 12, 1956
Creator:
Arabian, Donald D. & Schmeer, James W.
System:
The UNT Digital Library
Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4
Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date:
August 28, 1956
Creator:
Arbic, Richard G.
System:
The UNT Digital Library
Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4
Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date:
August 28, 1956
Creator:
Arbic, Richard G.
System:
The UNT Digital Library
Flight Test of a Solid-Fuel Ram Jet With the Internal Surface of the Combustor Air Cooled
Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. Having an internally cooled combustor averted combustor burn-out during the flight test. Results regarding acceleration, altitude, air specific impulse, and fuel specific impulse are provided.
Date:
July 3, 1956
Creator:
Bartlett, Walter A., Jr.
System:
The UNT Digital Library
Flight Test of a Solid-Fuel Ramjet With the Internal Surface of the Combustor Air Cooled
Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
Date:
July 3, 1956
Creator:
Bartlett, Walter A., Jr.
System:
The UNT Digital Library
Temperature Drops Through Liquid-Cooled Turbine Blades With Various Cooling-Passage Geometries
Memorandum presenting the effects of variations in cooling-passage geometry on the relations between heat flow and temperature drops within liquid-cooled turbine blades. Wall thicknesses, blade section depths, and cooling-passage sizes, shapes, and spacings were varied experimentally on a simple electric analog on which are simulated rectangular sections of blades. Results are presented in terms of temperature differences between the cooled-surface temperature and average heated-surface temperature, minimum heated-surface temperature, maximum heated-surface temperature, and maximum temperature at the centerline of the turbine blades.
Date:
March 23, 1956
Creator:
Bartoo, Edward R.
System:
The UNT Digital Library
Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies With Conical Flares and Extensive Flow Separation
Report presenting an investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions at Mach number 6.8. Information about flow characteristics, flare drag, and the relationship between flare drag and flare heating is provided.
Date:
July 20, 1956
Creator:
Becker, John V. & Korycinski, Peter F.
System:
The UNT Digital Library
Experimental investigation of the effect of boundary-layer transition on the average heat transfer to a yawed cylinder in supersonic flow
Report presenting the average heat-transfer to the forward half of a circular cylinder measured in a blowdown jet at a stream Mach number of 4.15. Most of the tests was made at a wall-to-stagnation temperature ratio of about 0.8. Report presenting pressure distributions, heat transfer and recovery temperatures, and effect of yaw on transition are provided.
Date:
July 13, 1956
Creator:
Beckwith, Ivan E. & Gallagher, James J.
System:
The UNT Digital Library
Performance of Variable Two-Dimensional Inlet Designed for Engine-Inlet Matching 1 - Performance at Design Mach Number of 3.07
Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.
Date:
November 20, 1956
Creator:
Beheim, M. A. & Gertsma, L. W.
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
Effects of Rocket-Armament Exhaust Gas on the Performance of a Supersonic-Inlet J34-Turbojet-Engine Installation at Mach 2.0
Report presenting an investigation of the effects of rocket-armament-exhaust-gas ingestion on the performance of a supersonic-inlet J34-turbojet-engine installation at Mach 2. Rockets were fired from two different spike positions and with the engine at high or low speed. Results regarding engine air flow, temperature, and flame-out are provided.
Date:
February 20, 1956
Creator:
Beheim, Milton A. & Evans, Phillip 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
An investigation of the aerodynamic characteristics at transonic Mach numbers of a swept-wing supersonic bomber configuration
Report presenting an investigation of the aerodynamic characteristics of a swept-wing supersonic bomber configuration conducted in the 8-foot transonic tunnel. The wing had an aspect ratio of 3.5, taper ratio of 0.2, 47 degrees of sweepback of the 0.25-chord line, and airfoil sections which were 5.5 percent thick parallel to the plane of symmetry. Results regarding the longitudinal force characteristics, effects of wing incidence, a modified wing, various auxiliary wing devices, and horizontal-tail height are provided.
Date:
February 1, 1956
Creator:
Bielat, Ralph P. & Cooper, J. Lawrence
System:
The UNT Digital Library
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight
From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Date:
December 5, 1956
Creator:
Bielat, Ralph P.; Coffee, Claude W., Jr. & Petynia, William W.
System:
The UNT Digital Library