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 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Performance of a Single Fuel-vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Performance of a Single Fuel-vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Date: November 30, 1959
Creator: Smith, A. L. & Wear, J. D.
Description: Single fuel-vaporizing combustor with injectors adapted for gaseous hydrogen.
Contributing Partner: UNT Libraries Government Documents Department
Some Research on the Lift and Stability of Wing-Body Combinations

Some Research on the Lift and Stability of Wing-Body Combinations

Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.
Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary analysis of hydrogen-rich hypersonic ramjet operation

Preliminary analysis of hydrogen-rich hypersonic ramjet operation

Date: May 29, 1959
Creator: Breitwieser, R. & Morris, J. F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 21, 1959
Creator: Sadoff, Melvin & Stewart, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 15, 1959
Creator: Church, J. D.
Description: Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

Date: September 30, 1958
Creator: Heidmann, M F & Baker, Louis, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Off-Design Performance of Divergent Ejectors

Off-Design Performance of Divergent Ejectors

Date: September 30, 1958
Creator: Beheim, M. A.
Description: Off-design performance of divergent ejectors.
Contributing Partner: UNT Libraries Government Documents Department
Off-design performance of divergent ejectors

Off-design performance of divergent ejectors

Date: September 30, 1958
Creator: Beheim, Milton A
Description: None
Contributing 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

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

Date: September 30, 1958
Creator: Martz, C William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

Date: September 30, 1958
Creator: Baker, Louis, Jr & Steffen, Fred W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of highly reactive chemical additives to improve afterburner performance at altitude

Use of highly reactive chemical additives to improve afterburner performance at altitude

Date: September 30, 1958
Creator: Wanhainen, John P & Sivo, Joseph N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of highly reactive chemical additives to improve afterburner performance at altitude

Use of highly reactive chemical additives to improve afterburner performance at altitude

Date: September 30, 1958
Creator: Sivo, J. N. & Wanhainen, J. P.
Description: Liquid hydrogen and aluminum trimethyl as highly reactive chemical additives in turbojet afterburner to promote fuel combustion process.
Contributing Partner: UNT Libraries Government Documents Department
Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield

Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield

Date: September 28, 1958
Creator: Strass, H. K. & Goodman, V. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Date: September 26, 1958
Creator: Mugler, John P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89

Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89

Date: September 26, 1958
Creator: Bond, Aleck C.; Lee, Dorothy B. & Rumsey, Charles B.
Description: Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices

Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices

Date: September 26, 1958
Creator: Aoyagi, Kiyoshi & Hickey, David H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Date: September 26, 1958
Creator: Lampkin, Bedford A & Tunnell, Phillips J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external- compression inlet

Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external- compression inlet

Date: September 23, 1958
Creator: Cubbison, R. N. & Samanich, N. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external-compression inlet

Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external-compression inlet

Date: September 23, 1958
Creator: Cubbison, R W & Samanich, N E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Date: September 23, 1958
Creator: Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Date: September 23, 1958
Creator: Nettle, J. Cary
Description: A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Date: September 23, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
Contributing Partner: UNT Libraries Government Documents Department
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

Date: September 20, 1958
Creator: Heinle, D. R. & Turner, H. L.
Description: Effects of manual attack-display noise filtering on pilot tracking performance.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Date: September 17, 1958
Creator: Gloria, H. R.; Sarabia, M. F. & Syvertson, C. A.
Description: Aerodynamic performance characteristics and static stability and control of hypersonic glider with arrow planform wings.
Contributing Partner: UNT Libraries Government Documents Department
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