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The study of aerodynamic forces in hypersonic environments is important to ensure the safety and proper functioning of aerospace vehicles. ...In this paper, computational analysis has been performed on a blunt cone model to study the aerodynamic characteristics when hypersonic flow is allowed to pass through the model. The flow has a Mach number of 8.44 and the angle of attack is varied from 0º to 20º. ...This study helps in understanding the aerodynamic and stability characteristics of hypersonic vehicles at various angles of attack that is significantly different from those of the subsonic or supersonic vehicles.

Why are Aerospace & Defense Companies Embracing Additive Manufacturing? Simplifying Power Design with Modular Architectures The Role of DevSecOps in Modern Edge Systems Making Machines Curious Designing Multi-Channel Microwave Radio Systems Using Optical Interconnects Solving Military Satellite, Radar and 5G Communications Challenges with GaN-on-SiC MMIC Power Amplifiers Advanced Airborne Defensive Laser for Incorporation on Strike Fighter Aircraft A technical and operational analysis of an airborne "hard-kill" Ytterbium fiber laser-based anti-missile system for use on strike fighters. Additive Manufacturing Utilizing a Novel In-Line Mixing System for Design of Functionally Graded Ceramic Composites Exploring the development of a direct ink writing system with multimaterial and in-line mixing capabilities for printing inks composed of high solids-loaded ceramic particulate suspensions.

This Recommended Practice is intended to outline the design, installation, testing, and field maintenance criteria for a high temperature metal pneumatic duct system, for use as a guide in the aircraft industry. These recommendations are to be considered as currently applicable and necessarily subject to revision from time to time, as a result of the rapid development of the industry.

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.

This section presents methods and examples of computing the steady-state heating and cooling loads of aircraft compartments. In a steady-state process the flows of heat throughout the system are stabilized and thus do not change with time. In an aircraft compartment, several elements compose the steady-state air conditioning load.

The “Know My PT6” app is a digital gateway to maintenance recommendations and to the services and facilities that P&W offers through its global customer service network for engine maintainers, owners, operators and pilots. It is designed to help PT6 customers and operators optimize the performance and availability of their PT6-powered aircraft.

The Boeing Company is kicking off a new round of flight-testing to research approximately 50 technology projects related to safety, environmental sustainability, and passenger experience. More than a dozen partners are participating in the 2019 program.

The rapid shift of commercial focus toward LEO has resulted in thousands of new satellites. An expected growth in satellite constellations requires space-faring nations such as New Zealand to engage in monitoring and regulating satellite activity.

The Raytheon Company is testing a new artificial intelligence (AI) tool developed to help determine when the multi-mode radar installed on U.S. Air Force CV-22 tiltrotor aircraft is in need of service.

The fluid flow treated in this section is isothermal, subsonic, and incompressible. The effects of heat addition, work on the fluid, variation in sonic velocity, and changes in elevation are neglected. An incompressible fluid is one in which a change in pressure causes no resulting change in fluid density. The assumption that liquids are incompressible introduces no appreciable error in calculations, but the assumption that a gas is incompressible introduces an error of a magnitude that is dependent on the fluid velocity and on the loss coefficient of the particular duct section or piece of equipment. Fig. 1A-1 shows the error in pressure drop resulting from assuming that air is incompressible. With reasonably small loss coefficients and the accuracy that is usually required in most calculations, compressible fluids may be treated as incompressible for velocities less than Mach 0.2.

In the “What’s Next for Aerospace and Defense: A Vision for 2050” study, AIA, New York City-based McKinsey & Company, and other industry partners reveal a comprehensive 30-year, Industry 4.0 forecast of air travel and spaceflight based on improvements in automation and digitization, next-generation materials, alternative energy sources and storage, and increased data throughput.

SAE International has published a new recommended practice for assessing the amount of nonvolatile particulate matter (nvPM) that exits aircraft engine exhaust nozzles – ARP6481: Procedure for the Calculation of Non-Volatile Particulate Matter Sampling and Measurement System Losses and System Loss Correction Factors

Engineers at Boeing and NASA are collaborating on a lightweight, ultra-thin Transonic Truss-Braced Wing (TTBW) concept, designed to be more aerodynamic and fuel efficient than current designs, as part of the Subsonic Ultra Green Aircraft Research (SUGAR) program focusing on innovative aerospace concepts that reduce noise and emissions while enhancing performance.

NASA officials and engineers are prepping to fly the agency’s F/A-18 research aircraft over Galveston, Texas, using a “quiet thump” technique designed to reduce loud sonic booms typically associated with supersonic flight. This week’s test flight sets off a series of quiet supersonic research flights off the coast of Texas to test ways to measure supersonic aircraft sound levels and the community’s response to the supersonic acoustic experience.

Together, the companies will develop customized lightweight material systems and advanced manufacturing processes, such as metal additive manufacturing – also known as 3D printing – to advance current and next-generation aerospace and defense solutions, including new structures and systems not currently in existence.

Officials and engineers at Boeing in Seattle are offering a glimpse into their vision for hypersonic air travel. They have released, for the first time, images of one of the company’s hypersonic air vehicle concepts for potential military and commercial passenger transport. ...They have released, for the first time, images of one of the company’s hypersonic air vehicle concepts for potential military and commercial passenger transport.

In April, NASA took another major step toward reintroducing supersonic flight with an award to Lockheed Martin Aeronautics Company to design, build, and test a supersonic aircraft to reduce sonic boom.

This report covers engine tests performed in Altitude Test Facilities (ATFs) with the primary purpose of determining steady state thrust at simulated altitude flight conditions as part of the in-flight thrust determination process. As such it is complementary to AIR1703 and AIR5450, published by the SAE E-33 Technical Committee. The gross thrust determined using such tests may be used to generate other thrust-related parameters that are frequently applied in the assessment of propulsion system performance. For example: net thrust, specific thrust, and exhaust nozzle coefficients. The report provides a general description of ATFs including all the major features. These are: Test cell air supply system. This controls the inlet pressure and includes flow straightening, humidity and temperature conditioning. Air inlet duct and slip joint. Note that the report only covers the case where the inlet duct is connected to the engine, not free jet testing.

This document addresses many of the significant issues associated with effects of inlet total-pressure distortion on turbine-engine performance and stability. It provides a review of the development of techniques used to assess engine stability margins in the presence of inlet total-pressure distortion. Specific performance and stability issues that are covered by this document include total-pressure recovery and turbulence effects and steady and dynamic inlet total-pressure distortion.

Tests for this experiment were conducted using the West Virginia University (WVU) Hypersonic Arc Jet Wind Tunnel. A series of twelve N52 grade neodymium magnets were placed in different orientations around a steel toroid mounted around the arc jet’s exhaust plume.