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Analysis of fluorine addition to the vanguard first stage

Description: From Introduction: "This report presents data pertinent to the problem of boosting rocket performance by adding up to 30 percent liquid fluorine to the liquid oxygen of an existing oxygen-hydrocarbon rocket engine."
Date: January 24, 1957
Creator: Tomazic, William A.; Schmidt, Harold W. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department

Altitude Starting Tests of a Small Solid Propellant Rocket

Description: From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date: June 21, 1957
Creator: Sloop, John L. & Krawczonek, Eugene M.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the stability of the antisubmarine rocket MK 1 Mod 0

Description: Report presenting an investigation in the stability tunnel to determine the cause and a remedy for the instability in flight of the antisubmarine rocket Mk 1 Mod 0. The results indicated that the Magnus effects and their nonlinear variation with angle of attack are important factors in the stability of the missile. Results regarding the presentation of data, longitudinal characteristics, and lateral characteristics are provided.
Date: November 13, 1952
Creator: Lichtenstein, Jacob H. & Williams, James L.
Partner: UNT Libraries Government Documents Department

Spectrographic Analysis of Plasmajets: Progress Report 2

Description: Abstract: This is the second progress report on the work performed at Sandia Corporation in the use of spectrographic techniques in plasmajet diagnostics. Typical results of spectrographic data from argon and nitrogen plasmajets are included. For the argon jet, the results from line intensity measurements of ionized and unionized atoms generally give good information. However, results from hydrogen line broadening measurements indicate several unexplained discrepancies. For the nitrogen jet, the N2 (0, 0) and N2 (0, 1) bands from the first negative series were used to determine a rotational temperature.
Date: March 1963
Creator: Shipley, K. L.
Partner: UNT Libraries Government Documents Department

Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8

Description: Report presenting some experimental free-flight data at a range of Mach numbers regarding the normal force and pitching effectiveness of several small pulse rockets in the fuselage of a rocket propelled model. Wing-damping data was also obtained from the wing bending response to the pulse-rocket excitations, and longitudinal stability data was determined from the model response. Results regarding pulse-rocket effectiveness, wing damping, and model stability data are provided.
Date: September 30, 1958
Creator: Martz, C. William
Partner: UNT Libraries Government Documents Department

Ambient Pressure Determination at High Altitudes by Use of Free-Molecule Theory

Description: "Several methods (references 1 and 2) based on gas-dynamic principles are available for reducing such measurements. The results obtained by these methods are subject to the limitation of the gas-dynamic theory which is that the mean free path of the molecules between impacts, is small with respect to the measuring device. Inasmuch as no information on the subject is to present known to be available, the purpose of the present paper is to present a method based on the concept of free-molecule theory for use in connection with this problem" (p. 1).
Date: March 1949
Creator: Wiener, Bernard
Partner: UNT Libraries Government Documents Department

Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Partner: UNT Libraries Government Documents Department

Flight Investigation of 6.25-Inch-Diameter Deacon Rocket and 10-Inch-Scale Model Rocket

Description: "Flight tests were conducted at the NACA Pilotless Aircraft Research Station, Wallops Island, to determine the characteristics of the Allegany Ballistics Laboratory's 6.2inch-diameter Deacon and 10-inch-scale model solid-propellant rocket motors. The tests were performed to assist in the development of these rockets which were designed for, and urgently needed to propel supersonic research models and pilotless aircraft. The tests showed that the rocket motors functioned properly under various flight- acceleration loads over a range of pre-ignition grain temperatures" (p. 1).
Date: March 25, 1949
Creator: Watson, R. S.
Partner: UNT Libraries Government Documents Department

Some Reactor Physics in the Rover Project

Description: From abstract: "A general and systematic development of reactor computing methods and detailed application given in Report LAMS-2255 separately is supplemented in this report for a few specific systems of interest to the Rover program. Neutron cross sections, reactor description, and computed results are given for a reactor required to have a constant (radially) power distribution at high temperatures."
Date: September 1958
Creator: Mills, C. B.
Partner: UNT Libraries Government Documents Department

Propulsion by Reaction

Description: This report concerns propulsion by means of rockets. The author concerns himself mainly with efficiency of propulsion and he defines and mathematically expresses those efficiencies.
Date: June 1930
Creator: Roy, Maurice
Partner: UNT Libraries Government Documents Department

Some Measurements of Noise From Three Solid-Fuel Rocket Engines

Description: Report presenting a systematic investigation of the sound field of a 1,000-pound-thrust solid-fuel rocket and data on two other rockets of 900 and 5500 pounds of thrust, which were obtained at a few isolated field points. Each of the three rockets was found to produce spectra somewhat similar to those of subsonic jets, which were random and with an envelope which peaks in the lower part of the audible range.
Date: December 1954
Creator: Lassiter, Leslie W. & Heitkotter, Robert H.
Partner: UNT Libraries Government Documents Department

Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Effect of Fluid-System Parameters on Starting Flow

Description: Note presenting an analysis made to determine the effect of configuration parameters and valve area-time operating relations on the speed of response of the liquid flow and the suppressed suction head of the pump in a rocket motor. The configuration consisted of tank, pump, combustion chamber, valves, and lines, including a bypass line with a valve around the pump. Results regarding the effect of valve resistance-time history on pump suppression head and flow response time and effect of configuration parameters are provided.
Date: September 1957
Creator: Krebs, Richard P.
Partner: UNT Libraries Government Documents Department

Effects of Rocket-Armament Exhaust Gas on the Performance of a Supersonic-Inlet J34-Turbojet-Engine Installation at Mach 2.0

Description: 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.
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Description: "Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 80 deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle" (p. 1).
Date: September 10, 1958
Creator: Swanson, Andrew G.
Partner: UNT Libraries Government Documents Department

Flight Investigation of the Performance of a Two-Stage Solid-Propellant Nike-Deacon (DAN) Meteorological Sounding Rocket

Description: A flight investigation of two Nike-Deacon (DAN) two-stage solid-propellant rocket vehicles indicated satisfactory performance may be expected from the DAN meteorological sounding rocket. Peak altitudes of 356,000 and 350,000 feet, respectively, were recorded for the two flight tests when both vehicles were launched from sea level at an elevation angle of 75 degrees. Performance calculations based on flight-test results show that altitudes between 358,000 feet and 487,000 feet may be attained with payloads varying between 60 pounds and 10 pounds.
Date: July 1956
Creator: Heitkotter, Robert H.
Partner: UNT Libraries Government Documents Department

Theoretical analysis of the performance of a supersonic ducted rocket

Description: Report presenting calculated performance characteristics of a ducted rocket with gasoline and liquid oxygen as the fuel mixture and with a mass flow of 1 slug per second. Evaluations of net thrust, frontal area, thrust per unit frontal area, and specific fuel consumption are given for all of the flight conditions under which it might operate.
Date: February 13, 1948
Creator: Hensley, Reece V.
Partner: UNT Libraries Government Documents Department

GPS Tracking of High Power Model Rockets

Description: Poster presented as part of the Research Experiences for Teachers (RET) in Sensor Education, a National Science Foundation (NSF) funded grant project. This poster discusses research on GPS/GSM based tracking systems for the recovery of high power model rockets.
Date: 2013
Creator: Gscheidle, Karl H.; Hardy, Debra; Kulle, Gregory; Bih, Michael; Acevedo, Miguel F. & Kollipara, Naveen
Partner: UNT College of Engineering

Performance of Air-Launched T-40 Rocket Motors with Two Types of Igniter

Description: Air-launched firings of eight T-40 rockets have been made. An average total impulse of 22,870 pound-seconds was observed for four of the rounds mounted in cone-cylinder vehicles. Maximum velocities of over 5000 feet per second were observed for two of the rounds with approximately 70-pound pay loads.
Date: October 25, 1954
Creator: Disher, J. H.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket

Description: Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the arming propeller, the effect of adding a spoiler nose ring to a basic model, and the effect of changes in the spin rate are provided.
Date: July 6, 1954
Creator: Bird, John D. & Lichtenstein, Jacob H.
Partner: UNT Libraries Government Documents Department