A Bibliography of NACA Reports on Control of Turbojet Engines (open access)

A Bibliography of NACA Reports on Control of Turbojet Engines

Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
System: The UNT Digital Library
Experimental Drag Coefficients of Round Noses With Conical Windshields at Mach Number 2.72 (open access)

Experimental Drag Coefficients of Round Noses With Conical Windshields at Mach Number 2.72

"An exploratory investigation at Mach number 2.72 has been made to show the decrease in the drag of a round-nose model achieved by mounting a small cone on a rod ahead of the nose. The geometric parameters which were varied were the cone-base diameter, cone angle, and rod length. All models showed large decreases in drag compared to that of the round nose alone" (p. 1).
Date: June 28, 1955
Creator: Jones, Jim J.
System: The UNT Digital Library
Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners (open access)

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
System: The UNT Digital Library
An Investigation of Jet Effects on Adjacent Surfaces (open access)

An Investigation of Jet Effects on Adjacent Surfaces

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).
Date: June 28, 1955
Creator: Bressette, Walter E. & Faget, Maxime A.
System: The UNT Digital Library
Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins (open access)

Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins

Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
System: The UNT Digital Library
Investigation of wing characteristics at a Mach number of 1.53 2: swept wings of taper ratio 0.5 (open access)

Investigation of wing characteristics at a Mach number of 1.53 2: swept wings of taper ratio 0.5

Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Date: June 28, 1948
Creator: Vincenti, Walter G.; Van Dyke, Milton D. & Matteson, Frederick H.
System: The UNT Digital Library
Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4) (open access)

Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4)

Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Date: June 28, 1950
Creator: Disher, John H. & Rabinowitz, Leonard
System: The UNT Digital Library
Two-Spool Matching Procedures and Equilibrium Characteristics of a Two-Spool Turbojet Engine (open access)

Two-Spool Matching Procedures and Equilibrium Characteristics of a Two-Spool Turbojet Engine

Memorandum presenting two-spool matching procedures which may be employed to analyze turbojet, turboprop, and stationary power plants. The procedures were applied to obtain the sea-level static equilibrium performance of a simple two-spool turbojet engine in which the compressor and turbine performances were based on experimental results. Results regarding engine performance at sea-level static conditions, component performance, and effect of compressor-discharge bleed are provided.
Date: June 28, 1954
Creator: Dugan, James F., Jr.
System: The UNT Digital Library
Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 4: stage and blade-row performance of stage with axial-discharge stators (open access)

Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 4: stage and blade-row performance of stage with axial-discharge stators

Report presenting an investigation to determine the performance characteristics of a transonic stage designed to produce transonic inlet Mach numbers relative to a succeeding stage. Results regarding rotor performance, stator performance, and stage performance are provided.
Date: June 28, 1954
Creator: Sandercock, Donald M.; Lieblein, Seymour & Schwenk, Francis C.
System: The UNT Digital Library
An Investigation of Jet Effects on Adjacent Surfaces (open access)

An Investigation of Jet Effects on Adjacent Surfaces

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).
Date: June 28, 1955
Creator: Bressette, Walter E. & Faget, Maxime A.
System: The UNT Digital Library
An investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic and loading characteristics in sideslip on a 45 degree sweptback, untapered tail assembly as determined from force tests and integrated vertical-tail span loadings (open access)

An investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic and loading characteristics in sideslip on a 45 degree sweptback, untapered tail assembly as determined from force tests and integrated vertical-tail span loadings

Report presenting an investigation in the high-speed tunnel of the effects at high subsonic speeds of horizontal-tail height on the aerodynamic and loading characteristics in sideslip of a 45 degree sweptback, untapered tail assembly. Configurations investigated include the fuselage alone, the fuselage plus vertical tail, and with a horizontal tail mounted at 0, 50, and 100 percent vertical-tail span. Results regarding the lateral force coefficient, rolling-moment coefficient, and a comparison of experimental and theoretical results are provided.
Date: June 28, 1955
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
System: The UNT Digital Library
Investigation of the Effects of an Airfoil Section Modification on the Aerodynamic Characteristics at Subsonic and Supersonic Speeds of a Thin Swept Wing of Aspect Ratio 3 in Combination With a Body (open access)

Investigation of the Effects of an Airfoil Section Modification on the Aerodynamic Characteristics at Subsonic and Supersonic Speeds of a Thin Swept Wing of Aspect Ratio 3 in Combination With a Body

Memorandum presenting a wind tunnel investigation to determine the effects of an airfoil section modification consisting of a greatly increased leading-edge radius and slight forward camber on the aerodynamic characteristics of a thin swept-wing-body combination at Mach numbers from 0.06 to 1.9. The tests showed that full-span modification of the wing resulted in very marked improvement in stability, drag, and high-lift characteristics for the configuration at low speeds due to the maintenance of attached flow over the wing to high lift coefficients.
Date: June 28, 1955
Creator: Graham, David & Evans, William T.
System: The UNT Digital Library
Experimental and analytical investigation of an acceleration regulating control for a turbojet engine (open access)

Experimental and analytical investigation of an acceleration regulating control for a turbojet engine

Report presenting an acceleration control that operates on fuel flow and uses directly measured acceleration as the control signal as applied to an axial-flow turbojet engine. A study to determine the feasibility and dynamic characteristics of the control was undertaken. Results regarding the open-loop characteristics and closed-loop characteristics are provided.
Date: June 28, 1956
Creator: Stiglic, Paul M.; Heppler, Herbert & Novik, David
System: The UNT Digital Library
Stability of supersonic inlets at Mach 1.91 with air injection and suction (open access)

Stability of supersonic inlets at Mach 1.91 with air injection and suction

Report presenting the stability characteristics of an axisymmetric conical inlet with supercritical spillage. Either injection or suction through the slot increased the stable subcritical range over that of the unmodified cone as much as 22 percent of the free-stream mass flow. Results regarding the effect of spike tip translation on inlet performance, effect of air injection and suction, secondary-flow requirements, comparison of various stabilizing methods, and effect of stabilizing devices on flow distortion are provided.
Date: June 28, 1956
Creator: Kowalski, K. & Piercy, Thomas G.
System: The UNT Digital Library
Full-scale evaluation of some flameholder design concepts for high-inlet-velocity afterburners (open access)

Full-scale evaluation of some flameholder design concepts for high-inlet-velocity afterburners

Report presenting an investigation of a full-scale afterburner with high burner-inlet velocity to determine burner performance with several variations in burner design. A total of 12 flameholder configurations were investigated at a specified burner-inlet velocity and a range of burner-inlet pressures. Results indicated that a basic annular two-V-gutter flameholder can operate at 90 to 95 percent combustion efficiency for fairly optimum burner length and pressure.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
System: The UNT Digital Library
Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins (open access)

Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

An investigation of the use of fins to prevent high-frequency combustion-pressure oscillations (screaming) in the combustion chamber of a 1000-pound-thrust rocket engine with a chamber pressure of 300 pounds per square inch and using liquid oxygen and n-heptane as propellants. Tangential combustion-pressure oscillations were found to be eliminated with longitudinal fins located in the combustion zone. Results regarding engine performance, effect of fins, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
System: The UNT Digital Library
Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio (open access)

Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio

"Slender-body aerodynamic theory is used in conjunction with thin-plate theory in the flutter analysis of low-aspect-ratio rectangular wings of constant thickness when chordwise variations of deflections are considered. The spanwise variation of deflection is given by a parabola, and the chordwise variation is allowed complete freedom. The results show the variation of flutter speed and mode shape with aspect ratio" (p. 1).
Date: June 28, 1957
Creator: Fralich, Robert W.; Hedgepeth, John M. & Tuovila, W. J.
System: The UNT Digital Library
Low-Speed Cascade Investigation of Thin Low-Camber Naca 65-Series Blade Sections at High Inlet Angles (open access)

Low-Speed Cascade Investigation of Thin Low-Camber Naca 65-Series Blade Sections at High Inlet Angles

Report presenting an investigation of 6-percent-thick NACA 65-series compressor blade sections in a two-dimensional porous-wall cascade tunnel at several lift coefficients, angles of attack, and solidities. The useful operating angle-of-attack range was generally found to decrease as inlet angle increases.
Date: June 28, 1957
Creator: Emery, James C.
System: The UNT Digital Library
Flight-determined induction-system and surge characteristics of the YF-102 airplane with a two-spool turbojet engine (open access)

Flight-determined induction-system and surge characteristics of the YF-102 airplane with a two-spool turbojet engine

Report presenting a brief compressor-surge and pressure-recovery program for the Convair YF-102 with a two-spool turbojet engine. The study covered a range of altitudes and Mach numbers.
Date: June 28, 1957
Creator: Saltzman, Edwin J.
System: The UNT Digital Library
Spin Tests of 1/20-Scale Models of the Chance Vought Revised XF6U-1 and F6U-1 Airplanes, TED No. NACA 2390 (open access)

Spin Tests of 1/20-Scale Models of the Chance Vought Revised XF6U-1 and F6U-1 Airplanes, TED No. NACA 2390

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on the 1/20-scale model of the Chance Vought XF6U-1 airplane altered to represent the XF6U-1 airplane as it will be spin-tested in flight, and also altered to represent the F6U-1 airplane as it will be produced for service use. Spin tests were made to determine the effects of control settings and movements at the normal loading. The results show that the spins obtained on the revised XF6U-1 airplane will be oscillatory in roll and yaw and that recoveries by rudder reversal will be rapid" (p. 1).
Date: June 28, 1948
Creator: Klinar, Walter J. & Berman, Theodore
System: The UNT Digital Library