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An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes
Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.
Date:
April 21, 1959
Creator:
Sadoff, Melvin & Stewart, John D.
System:
The UNT Digital Library
Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50
Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.
Date:
April 15, 1959
Creator:
Church, James D.
System:
The UNT Digital Library
Comparison of Various Heat Exchangers for Liquid-Metal Nuclear Turbojet Over Range of Flight and Operating Conditions
Memorandum presenting an analysis of a large number of liquid-metal-to-air heat-exchanger cores for the nuclear-powered liquid-metal turbojet cycle to determine which types yield the best overall net thrust per total engine weight. The performances of all exchangers considered were initially evaluated at a median condition. The performance of the best of each of the four types was compared with that of a shell-and-tube exchanger with the air flowing through the tubes, operating at the same condition.
Date:
April 28, 1958
Creator:
Ragsdale, Robert G.
System:
The UNT Digital Library
Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
Date:
April 23, 1958
Creator:
Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
System:
The UNT Digital Library
Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane
From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
Date:
April 23, 1958
Creator:
Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
System:
The UNT Digital Library
Effect of control trailing-edge thickness or aspect ratio on the oscillating hinge-moment and flutter characteristics of a flap-type control at transonic speeds
Report presenting free-oscillation tests in the high-speed tunnel to determine the effect of control trailing-edge thickness and control aspect ratio on the dynamic hinge-moment characteristics of a trailing-edge, flap-type control. Tests were made at a range of Mach numbers and a range of oscillation reduced frequency at an angle of attack of 0 degrees. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date:
April 23, 1958
Creator:
Moseley, William C., Jr. & Thompson, Robert F.
System:
The UNT Digital Library
Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds
Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date:
April 23, 1958
Creator:
Moseley, William C., Jr. & Thompson, Robert F.
System:
The UNT Digital Library
Ground Simulator Studies of a Small Side-Located Controller in a Power Control System
Memorandum presenting an investigation to determine the operating characteristics of a small side-located control stick with the use of a ground simulator incorporating a power control system. The simulator or pitch chair was designed to produce the pitching motion associated with the short-period mode of an airplane. The general opinion of all of the pilots operating the pitch chair was that they were favorably impressed with their ability to precisely track with the small side-located controller provided the control-system characteristics were desirable.
Date:
April 23, 1958
Creator:
Assadourian, Arthur
System:
The UNT Digital Library
Low-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flaps
Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of spoilers on the static longitudinal and lateral aerodynamic characteristics and the chordwise pressure distribution on a thin, untapered, unswept, semispan wing with an aspect ratio of 3.33 and NACA 65A004 airfoil sections. Results are presented in the form of static longitudinal and lateral aerodynamic characteristics and tabulated pressure coefficients, section normal-force coefficients, and section pitching-moment coefficients.
Date:
April 23, 1958
Creator:
Croom, Delwin R.
System:
The UNT Digital Library
Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date:
April 22, 1958
Creator:
Kerslake, William R.
System:
The UNT Digital Library
An analysis of surface pressures and aerodynamic load distribution over the swept wing of the Douglas D-558-II research airplane at Mach numbers from 0.73 to 1.73
Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.
Date:
April 21, 1958
Creator:
Taillon, Norman V.
System:
The UNT Digital Library
Free-Flight Investigation to Determine the Inlet External Drag of Four Inlet Models at Mach Numbers From 1.50 to 3.00
Memorandum presenting a free-flight investigation conducted on four supersonic nose inlets. Each inlet used conical-shock and isentropic-compression center bodies; two of the models had internal contraction and two did not. Results regarding drag coefficient, pressure recovery, mass-flow ratio, and Reynolds number range are provided.
Date:
April 21, 1958
Creator:
Kouyoumjian, Walter L.
System:
The UNT Digital Library
Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities
Report presenting testing of specimens of various metals in selected geometric configurations exposed to liquid fluorine under controlled conditions of flow and pressure. None of the samples eroded, decomposed, or exhibited any measurable physical or chemical changes.
Date:
April 17, 1958
Creator:
Schmidt, Harold W.
System:
The UNT Digital Library
Incipient spin characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA AD 3118
Report presenting an investigation of the incipient spin characteristics of a 1/25-scale dynamic model of the Chance Vought XF8U-1 airplane. The model was launched by a catapult apparatus into free flight at the angle of attack and airspeed correspond to stall with various control settings and was loaded as lightly as possible because of the limitations of the catapult apparatus. Results regarding the basic data and effects of modifications are provided.
Date:
April 17, 1958
Creator:
Healy, Frederick M.
System:
The UNT Digital Library
Effects of nose and afterbody modifications on aerodynamic characteristics of a body with and without a vertical tail at a Mach number of 2.01
Report presenting the effects at Mach number 2.01 of various changes in nose and afterbody shape on the static aerodynamic characteristics of a body of revolution with a fineness ratio of 11 with an ogive nose, a cylindrical center section, and a boattail or cylindrical afterbody. Some body conditions were tested in combination with a vertical tail. Results regarding the effects of nose and afterbody modifications and vertical tail-on configurations are provided.
Date:
April 15, 1958
Creator:
Foster, Gerald V.
System:
The UNT Digital Library
Effects of shock-boundary-layer interaction on the performance of a long and a short subsonic annular diffuser
Report presenting an investigation to determine the effects on performance of positioning normal shocks in or upstream of both a long and a short subsonic annular diffuser. Results regarding the entrance flow conditions, performance for subsonic-entrance flows, and performance with choked- and supersonic-entrance flows are provided.
Date:
April 15, 1958
Creator:
Wood, Charles C. & Henry, John R.
System:
The UNT Digital Library
An Exploratory Investigation at Mach Numbers of 2.50 and 2.87 of a Canard Bomber-Type Configuration Designed for Supersonic Cruise Flight
Report presenting results for a canard bomber-type configuration designed for supersonic cruise flight at Mach numbers 2.50 and 2.87 and over a range of angles of attack and angles of sideslip. Results regarding longitudinal characteristics and lateral stability are provided. The original configuration was directionally unstable at low angles of attack, but satisfactory directional stability could be obtained using upper-surface vertical fins.
Date:
April 15, 1958
Creator:
Kelly, Thomas C.; Carmel, Melvin M. & Gregory, Donald T.
System:
The UNT Digital Library
Jet effects on the base drag of a cylindrical afterbody with extended nozzles
A wind-tunnel investigation to determine the effects of both single and twin jets on base drag of a cylindrical body has been conducted at Mach numbers from 0.6 to 1.4. The plane of the jet exit was varied with respect to that of the afterbody. Jet total-pressure ratio ranged up to 20. Significant improvements in base drag were obtained by extending the plane of the jet exits beyond the afterbody base and by venting the base cavity to the external stream.
Date:
April 15, 1958
Creator:
Nelson, William J. & Scott, William R.
System:
The UNT Digital Library
Preliminary Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane
Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.
Date:
April 15, 1958
Creator:
Jones, George W., Jr. & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.
Date:
April 15, 1958
Creator:
Jones, George W., Jr. & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.
Date:
April 15, 1958
Creator:
Smith, Samuel L., III & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Report presenting a transonic flutter investigation of models of the wing of a fighter airplane. Results regarding the wings with and without leading-edge chord-extensions, and scaling of the stiffness are presented. The flutter boundary was found to remain below sea level with or without the leading-edge extensions.
Date:
April 15, 1958
Creator:
Smith, Samuel L., III & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date:
April 11, 1958
Creator:
Weber, Richard J. & Connolley, Donald J.
System:
The UNT Digital Library
Preliminary Analysis of a Nuclear-Powered Supersonic Airplane Using Ramjet Engines
Report presenting performance estimates for a family of airplanes designed to cruise at Mach number 4.25 and using General Electric AC-210 ramjet engines. The airplane was designed to carry a payload of 10,000 pounds and use a crew of one. Results regarding the shield weight, engine weight, number of engines, and nozzle-velocity coefficient are provided.
Date:
April 11, 1958
Creator:
Weber, Richard J. & Connolley, Donald J.
System:
The UNT Digital Library