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Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85
Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date:
March 18, 1953
Creator:
Dickey, Robert R. & Spahr, J. Richard
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
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
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
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.
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.
System:
The UNT Digital Library
Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation
Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
Date:
March 9, 1953
Creator:
Spooner, Robert B.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control
Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
Date:
January 12, 1953
Creator:
Smith, Willard G.
System:
The UNT Digital Library
An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds
Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date:
August 21, 1953
Creator:
Henry, Beverly Z., Jr. & Braden, John A.
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant
Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
February 6, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Liquid Ammonia and Liquid Fluorine as a Rocket Propellant
"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).
Date:
July 3, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Mixtures of Liquid Ammonia and Hydrazine as Fuel With Liquid Fluorine as Oxidant for Rocket Engines
Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
July 29, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrazine and Liquid Fluorine as a Rocket Propellant
"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).
Date:
July 3, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53
Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date:
September 28, 1953
Creator:
Bland, William M., Jr. & Nelson, Robert L.
System:
The UNT Digital Library
Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios
Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date:
August 18, 1953
Creator:
Whitcomb, Richard T. & Fischetti, Thomas L.
System:
The UNT Digital Library
Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches
Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date:
April 9, 1953
Creator:
Bihrle, William, Jr. & Stone, Ralph W., Jr.
System:
The UNT Digital Library
Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil
"Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice" (p. 1).
Date:
June 22, 1953
Creator:
Gray, Vernon H. & Bowden, Dean T.
System:
The UNT Digital Library
Experimental Investigation of Radome Icing and Icing Protection
Memorandum presenting an investigation conducted in the icing research tunnel to determine the icing characteristics, the effects of icing on radar operation, and the protection requirements for two radome configurations. The radomes were for the F-89 airplane and were investigated at airspeeds up to 290 miles per hour, air total temperatures from -15 to 20 degrees Fahrenheit, water contents up to 1.0 gram per cubic meter, and angles of attack of 0 and 4 degrees.
Date:
January 20, 1953
Creator:
Lewis, James P. & Blade, Robert J.
System:
The UNT Digital Library
Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0
Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date:
June 15, 1953
Creator:
Smolak, George R. & Wentworth, Carl B.
System:
The UNT Digital Library
Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution
Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.
Date:
December 15, 1953
Creator:
Loftin, Laurence K., Jr. & Horton, Elmer A.
System:
The UNT Digital Library
Investigation of Aerodynamic and Icing Characteristics of a Flush Alternate Inlet Induction System Air Scoop
"An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet" (p. 1).
Date:
July 24, 1953
Creator:
Lewis, James P.
System:
The UNT Digital Library
De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding
Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date:
May 25, 1953
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner
"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).
Date:
August 6, 1953
Creator:
von Glahn, U.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing
Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date:
July 8, 1953
Creator:
Phelps, E. Ray
System:
The UNT Digital Library