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Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, W. E., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Date: August 11, 1958
Creator: Stoney, William E., Jr.
Partner: UNT Libraries Government Documents Department

Flight, analog-simulator, and analytical studies of an automatically controlled interceptor which uses a bank-angle-error computer for lateral commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Partner: UNT Libraries Government Documents Department

Stability of ballistic reentry bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

Description: Report presenting a 45 degree sweptback wing of aspect ratio 3, with twist and a distributed type of camber, tested in combination with a body of fineness ratio 12.5 to determine the lift, drag, and pitching-moment characteristics.
Date: August 11, 1958
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Partner: UNT Libraries Government Documents Department

Effect of Dissociation on Exhaust-Nozzle Performance

Description: Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Examinations of the dissociation products involved and the energies associated with them, for the hydrocarbon- and hydrogen-air mixtures indicated that a major portion of the dissociation energy for the hydrocarbon mixture is involved in the carbon monoxide molecule.
Date: June 11, 1958
Creator: Reynolds, T. W.
Partner: UNT Libraries Government Documents Department

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. The purpose behind the investigation was to investigate the idea that luminous radiation from nongaseous substances in the afterburner gas stream might be present and vary significantly with pressure.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Performance of JP-4 fuel with fluorine-oxygen mixtures in 1000-pound-thrust rocket engines

Description: Report presenting seven injectors of four different types tested for use with JP-4-oxygen-fluorine propellant combinations. High characteristics velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding the injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Preliminary analysis of a nuclear-powered supersonic airplane using ramjet engines

Description: 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.
Partner: UNT Libraries Government Documents Department

Preliminary analysis of a nuclear powered supersonic airplane using ramjet engines

Description: 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.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel investigation of a 1/28-scale model of the North American FJ-4 airplane: TED No. NACA AD-3112

Description: Report presenting an investigation in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/28-scale dynamic model of the North American FJ-4 airplane. Results indicated that either a flat-type or a steep-type spin maybe obtained when the airplane is spinning erect. Results regarding inverted spins, loading condition, spin-recovery rocket tests, and spin-recovery parachute tests are provided.
Date: February 11, 1958
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79

Description: From Summary: "Incipient spin characteristics have been investigated on a 1/35-scale dynamic model of the Convair F-102A airplane. The model was launched by a catapult apparatus into free flight with various control settings, and the motions obtained were photographed. The model was ballasted for the combat loading. All tests were made with the speed brakes and landing gear retracted, and engine effects were not simulated."
Date: February 11, 1958
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Performance evaluation of reduced-chord rotor blading as applied to J23 two-stage turbine 6: stage performance with standard rotor blading at inlet conditions of 35 inches of mercury absolute and 700 degrees R

Description: Report presenting an evaluation of the stage performance of the J73 turbine on the basis of previous performance investigations of the first stages alone and of the two-stage turbines with standard and with reduced-chord rotor blading for a range of rotational speeds and pressure ratios. The results demonstrated that both of the two-stage turbines and first-stage turbines had comparable performance.
Date: July 11, 1957
Creator: Davidson, Elmer H. & Schum, Harold J.
Partner: UNT Libraries Government Documents Department

Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine

Description: The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage so that the first stage of the unit could be operated independently. The modified single-stage turbine was then operated over a range of stage pressure ratio and speed. The single-stage turbine operated at a peak brake internal efficiency of over 90 percent at an over-all stage pressure ratio of 1.4 and at 90 percent of design equivalent speed. Furthermore, the unit operated at high efficiencies over a relatively wide operating range. When the single-stage results were compared with the multistage results at the design operating point, it was found that the first stage produced approximately half the total multistage-turbine work output.
Date: July 11, 1957
Creator: Schurn, Harold J.
Partner: UNT Libraries Government Documents Department

Performance evaluation of reduced-chord rotor blading as applied to J73 two-stage turbine 1: over-all performance with standard rotor blading at inlet conditions of 35 inches of mercury absolute and 700 degrees R

Description: Report presenting an investigation conducted to determine the overall performance of the J73 two-stage turbine with a standard rotor-blade configuration. The turbine operated with a maximum brake internal efficiency between 0.91 and 0.92 at an overall pressure ratio of about 3.4 and 120 percent equivalent design rotor speed. Results regarding the overall performance, variation of equivalent weight flow with overall pressure ratio, and effect of limiting blade loading are provided.
Date: July 11, 1957
Creator: Berkey, William E.; Rebeske, John J., Jr. & Forrette, Robert E.
Partner: UNT Libraries Government Documents Department

Performance evaluation of reduced-chord rotor blading as applied to J73 two-stage turbine 2: over-all performance at inlet conditions of 35 inches of mercury absolute and 700 degrees R

Description: Report presenting an investigation to determine the feasibility of utilizing a reduced-chord rotor blading on the two-stage turbine of the J73 turbojet engine in order to reduce the weight. The turbine was operated as a component over a range of speeds and overall pressure ratios at turbine-inlet conditions corresponding to 35 inches of mercury absolute and 700 degrees R. Results regarding the overall performance, performance map, and peak efficiency are provided.
Date: July 11, 1957
Creator: Schum, Harold J.; Rebeske, John J., Jr. & Forrette, Robert E.
Partner: UNT Libraries Government Documents Department

Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Description: Report presenting an investigation of an axial-flow compressor rotor with an inlet hub-tip radius ratio of basically zero. Results regarding the radial distribution of total-pressure ratio and efficiency, measured pressure ratio at design speed, weight flow, and low-speed cascade data are provided.
Date: March 11, 1957
Creator: Westphal, Willard R. & Maynard, John W., Jr.
Partner: UNT Libraries Government Documents Department

Flight-determined static lateral stability and control characteristics of a swept-wing fighter airplane to a Mach number of 1.39

Description: Report presenting an investigation of the static lateral stability characteristics of a swept-wing fighter-type airplane with three vertical-tail configurations and two wing configurations at an altitude of 40,000 feet over a range of Mach numbers. Data was obtained in several conditions, including constant-heading sideslips and wings-level turns, aileron rolls, and abrupt rudder pulses. Results regarding the sideslip characteristics, lateral control, and control effectiveness derivatives are provided.
Date: March 11, 1957
Creator: Matranga, Gene J. & Peele, James R.
Partner: UNT Libraries Government Documents Department

The influence of imperfect radar space stabilization on the final attack phase of an automatic interceptor system

Description: From Summary: "The manner in which imperfect space stabilization of the tracking radar influences the flight path stability of an automatic interceptor during the attack phase is illustrated by means of flight and analog-computer time histories. It is shown analytically that these effects may be interpreted in terms of a destabilizing airplane rate feedback which can be canceled by an additional compensatory feedback in the radar tracking loop."
Date: March 11, 1957
Creator: Triplett, William C.; McLean, John D. & White, John S.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the combustion of a 50 percent pentaborane - 50 percent JP-4 fuel blend in a turbojet combustor at simulated altitude conditions

Description: A preliminary investigation was conducted to determine the combustion characteristics of a fuel composed of 50 percent pentaborane and 50 percent JP-4 (MIL-F-5624A) by weight in a turbojet combustor. A combustor designed to fit the housing of a J33-A-23 turbojet engine was selected for convenience. The fuel was evaluated at two engine conditions simulating altitudes of 40,000 and 57,000 feet, an engine speed of 85 percent of rated rpm, and a flight Mach number of 0.6. The pentaborane blend was initially evaluated in combustors developed for pure pentaborane and diborane reported in NACA RM E53B18 and RM E52L15. The performance of the blend was unsatisfactory in these combustors. A new combustor was then developed which provided combustor efficiencies measured from 91 to 101 percent as compared with efficiencies of 92 to 94 percent previously obtained for pentaborane at comparable conditions. Additional refinements of design details are needed to obtain lower oxide deposits and a more uniform outlet temperature profile; however, the combustor is believed to incorporate some of the design principles required to obtain satisfactory over-all performance with the fuel blend investigated.
Date: March 11, 1957
Creator: Branstetter, J. Robert; Kaufman, Warner B. & Gibbs, James B.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64

Description: From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Date: September 11, 1956
Creator: Swanson, Andrew G. & Rumsey, Charles B.
Partner: UNT Libraries Government Documents Department