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The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.

The art and science of thrust vectoring technology has seen a gradual shift towards fluidic thrust vectoring techniques owing to the potential they have to greatly influence the aircraft propulsion systems. The prime motive of developing a fluidic thrust vectoring system has been to reduce the weight of the mechanical thrust vectoring system and to further simplify the configuration. ...The art and science of thrust vectoring technology has seen a gradual shift towards fluidic thrust vectoring techniques owing to the potential they have to greatly influence the aircraft propulsion systems. ...Aircrafts using vectored thrust rely to a lesser extent on aerodynamic control surfaces such as ailerons or elevator to perform various maneuvers and turns than conventional-engine aircrafts and thus have a greater advantage in combat situations. Fluidic thrust vectoring systems manipulate the primary exhaust flow with a secondary air stream which is typically bled from the engine compressor or fan.

This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.

Aviation propulsion development continues to rely upon fossil fuels for the vast majority of commercial and military applications. ...With those challenges in mind, research and development of more efficient and electric propulsion systems will expand. Fuel-cell technology is but one example that addresses such emission and resource challenges, and others, including negligible acoustic emissions and the potential to leverage current infrastructure models. ...Requirements for greater flight time, stealth characteristics, and thrust-to-power ratios adds urgency to the development of efficient propulsion methods for applications such as UAVs, which looks to technologies such as asymmetrical capacitors to enhance electric propulsion efficiency.

This paper presents the results of a multi-year project by the Naval Air Development Center to design, fabricate, evaluate, and flight test a fluidic flight control system in a Navy T-2C, a twin-jet carrier aircraft. The work leading to this flight test began with component design to the aircraft installation constraints and to flight requirements, continued through fabrication, laboratory testing and system installation, and culminated with man-in-the-loop evaluation of the system installed in the aircraft, ground tests, and flight. ...The results of these tests demonstrate the successful integration of three advanced technologies: 8000-psi actuationcontrolled both by fluidics and fly-by-wirewhich the Naval Air Development Center has brought to fruition.

This paper describes the concept and development of an all fluid (hydraulic) system for yaw axis stability augmentation of a commercial jet aircraft. This unique system uses a fluidic accelerometer as a sensor, a bellows actuated flapper nozzle circuit for signal amplification, and a conventional spool type power stage driving an actuator with mechanical position feedback. ...This unique system uses a fluidic accelerometer as a sensor, a bellows actuated flapper nozzle circuit for signal amplification, and a conventional spool type power stage driving an actuator with mechanical position feedback. ...The system replaces a rate sensor and differentation network and most of the signal amplification stages found in more conventional fluidic stability augmentation systems. A complete analog simulation, along with prototype testing, was performed to insure the required performance of the final design.

This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs). ...This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs).

The Equipped Avionics Bay of the Automated Transfer Vehicle is thermally controlled by means of ten Active Fluidic Cooling Units (AFCU), each of them being composed of four Variable Conductance Heat Pipes (VCHP).

The impetus for this investigation stems from the expanding implementation of fluidics in aircraft, ground vehicle, and helicoper controls. The feasibility of a fluidic stabilization system for low-pressure pneumatic/hydraulic operation has been demonstrated(1)*. ...An experimental investigation was conducted to determine the feasibility of a high-pressure (4000 psig) hydraulic fluidic vortex rate sensor. The impetus for this investigation stems from the expanding implementation of fluidics in aircraft, ground vehicle, and helicoper controls. ...In such a system, the vehicle's angular rate is sensed by a low-pressure fluidic vortex rate sensor. Greater overall system simplicity can be achieved by direct utilization of the high-pressure hydraulic fluid from the helicopter's primary hydromechanical system.

This paper presents the overall scope of the NASA Lewis High Performance Aircraft Propulsion Research Program. High performance fighter aircraft of interest include supersonic fighters with such capabilities as short takeoff and vertical landing (STOVL) and/or high maneuverability. ...The NASA Lewis effort involving STOVL propulsion systems is focused primarily on component-level experimental and analytical research. ...The overall objective of the NASA Inlet Experiments portion of the HATP, which NASA Lewis leads, is to develop and enhance inlet technology that will ensure high performance and stability of the propulsion system during aircraft maneuvers at high angles of attack. To accomplish this objective, both wind-tunnel and flight experiments are used to obtain steady-state and dynamic data, and computational fluid dynamics (CFD) codes are used for analyses.

This document is intended to serve as suitable guidance for propulsion system manufacturers and applicants for propulsion system type certification. It is also intended to provide guidance for subsequent propulsion system integration into aircraft systems for aircraft certification and operational use. ...The purpose of this SAE Aerospace Information Report (AIR) is to provide guidance for aircraft engine and propeller systems (hereafter referred to as propulsion systems) certification for cybersecurity. Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane. ...Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane.

During the 1970's, our hypersonic effort dwindled to a few dedicated research efforts which refined propulsion, aerodynamics, and computational fluid dynamics principles. To make real progress in the 1980's, and beyond, a focus and a rekindled effort was needed. ...The primary emphasis of the paper is National Aero-Space Plane propulsion technology. Key technical challenges are noted and a discussion of progress relative to those challenges associated with propulsion is presented. ...Key technical challenges are noted and a discussion of progress relative to those challenges associated with propulsion is presented.

Investigation into electric propulsion continues to be an area of hopeful research since the pioneering age of aviation. However, more recent global awareness of carbon emissions on the planet and the desire to create more efficient systems has reinvigorated new life into the field. ...Experimental studies on electric propulsion by virtue of asymmetrical electrodes, on a micro scale, have yielded potentially superior efficiency ratings when compared to currently adopted methods. ...The observed effect is that asymmetrical electrodes which are subjected to high voltage and are separated by a fluid dielectric medium experience thrust towards the smaller electrode. This method of propulsion is unique and possesses several features that differentiate it from conventional methods of propulsion.

The Waste Management/Rocket Propulsion System appears capable of satisfying many propulsion requirements; for example, orbit change maneuvers, aerodynamic drag makeup, midcourse correction, terminal braking, and auxiliary and emergency propulsion. ...To date, spacecraft designers have considered life support systems and rocket propulsion systems as independent subsystems of a manned spacecraft. The Integrated Waste Management/Rocket Propulsion System concept developed by Rocket Research Corp. under NASA Contract NAS 1–6750, has demonstrated that human waste products can form a useful propellant ingredient and provide propulsion, as well as be an effective means of removing and sterilizing spacecraft waste. ...The Integrated Waste Management/Rocket Propulsion System concept developed by Rocket Research Corp. under NASA Contract NAS 1–6750, has demonstrated that human waste products can form a useful propellant ingredient and provide propulsion, as well as be an effective means of removing and sterilizing spacecraft waste.

The wind tunnel experiments are conducted at a Reynolds number of Re=3.0·106. Fluidic oscillators are applied at the c-pillars and at the upper rear edge of the window. The actuators are installed inside the hollow designed model emitting a high frequency sweeping jet.

For the past few years an extensive experimental program to understand the fluid dynamics of the Space Shuttle Main Engine hot gas manifold has been in progress at Marshall Space Flight Center (MSFC).

This SAE Aerospace Recommended Practice (ARP) describes the multi-pass method for evaluating the filtration performance of fine lube filter elements, commonly utilized in aerospace power and propulsion lubrication systems: gas turbine engines, auxiliary power units (APUs), helicopter transmissions, constant speed drives (CSDs), and integrated drive generators (IDGs).

The Propulsion Aerodynamics Branch (and its predecessors) at the NASA Langley Research Center has been conducting propulsion aerodynamics research since 1941. ...The Propulsion Aerodynamics Branch (and its predecessors) at the NASA Langley Research Center has been conducting propulsion aerodynamics research since 1941. During that time, branch research has had an impact on almost every aircraft flown. ...During the last decade, computational fluid dynamics research has played an increasing role in branch contributions. This paper provides an overview of the propulsion/airframe integration activities conducted in the branch during the last several years and some indication of the direction of future research.

A rigorous propulsion system modelling method suitable for control and condition monitoring purposes is developed. ...Previously developed control oriented methods yielding nominal models for gaseous medium propulsion systems are extended to include both nominal and anomalous models for liquid mediums in the following two ways. ...First, thermodynamic and fluid dynamic properties for liquids such as liquid hydrogen are incorporated into the governing equations.

The simulation results reveal that jet injection, particularly for the regimes of jet injection velocity where significant drag reduction is achieved, and the scales of turbulence reduce close to the wing surface, highlighting that additional turbulence control measures are not required to implement fluidic winglets. The culmination of this study is that the implementation of fluidic winglets leads to a significant reduction in drag at low speeds for low aspect ratio wings. ...However, results reveal that fluidic on-demand winglets effectively reduce drag for low-speed flight regimes without the addition of any extra weight. ...This research aims to investigate the fluidic winglet jet characteristics on the aerodynamic performance of the wing. Results indicate that the spanwise blowing shifts the core of the wingtip vortices upward and outward from the wing surface.