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A scramjet exhaust simulation technique for hypersonic wind tunnel testing has been developed. Mixtures of Argon and Freon correctly match the inviscid simulation parameters of Mach number, static-pressure ratio, and the ratio of specific heats at the combustor exit location; this simulation is accomplished at significantly reduced temperatures and without combustion.

This Aerospace Information Report (AIR) addresses the subject of aircraft inlet-swirl distortion. A structured methodology for characterizing steady-state swirl distortion in terms of swirl descriptors and for correlating the swirl descriptors with loss in stability pressure ratio is presented. The methodology is to be considered in conjunction with other SAE inlet distortion methodologies. In particular, the combined effects of swirl and total-pressure distortion on stability margin are considered. However, dynamic swirl, i.e., time-variant swirl, is not considered. The implementation of the swirl assessment methodology is shown through both computational and experimental examples. Different types of swirl distortion encountered in various engine installations and operations are described, and case studies which highlight the impact of swirl on engine stability are provided. Supplemental material is included in the appendices.

Electrifying Aviation: The Path to Decarbonizing the Skies /Electric aviation mirrors the early stages of the electric vehicle revolution Advances in Military Avionics Technologies Create New Challenges for RF Test and Measurement Plasma Electrolytic Oxidation: The Future of Lightweight Designs in Aerospace and Defense Advanced RF Simulation Reduces Cost and Schedule Risk Assure 5G NTN Performance Before Launch In the complex and quickly evolving 5G NTN landscape, simulating, emulating, and evaluating RF systems boosts mission success. Qualification of Multi-Channel Direction Finding Radar Receivers in The Lab Bullet Impact Testing of Ammunition and Explosives at Picatinny Arsenal A bullet impact (BI) test for evaluating the response of energetically loaded items has been established at the U.S. Army Combat Capabilities Command (DEVCOM) Armaments Center (AC) Explosive Development Facility.

Using an Open Architecture Approach to Military Avionics Can Embedded Electronics Components Meet the Demands of Hypersonic Missiles? CMOSS/CMFF Trades Interoperability for Free-Thinking Innovation Exploring High-Performance Applications for Distributed Transport Property Thermoelectrics Heterogeneous Integration and SiPs Benefit SWaP-C Reduction The Future of Automated Guided Vehicles for Aerospace and Defense Next-generation AGVs are already starting to deliver labor and cost savings for the U.S. defense industry, and the commercial aerospace sector is watching closely Deep Reinforcement Learning Achieves Multifunctional Morphing Airfoil Control Smooth camber morphing aircraft offer increased control authority and improved aerodynamic efficiency.

From part to plane: the fastest machine wins Next-gen machining centers and controllers brings new precision and capabilities to both metal and composite manufacturing. Files moved around the world As aircraft manufacturers distribute more jobs to contractors, streamlining the transfer of information has become an important part of both design and manufacturing. Top technologies of 2008 A look back at some of the most significant technological innovations during the past year. VLJ power Some engine programs for very light jets are full swing while certification awaits others.

Simulation solves C5 cargo door problem Dynamic analysis software allows engineers to solve fatigue-related problems without prototypes. UAV development Although unmanned aerial vehicles (UAVs) have been employed successfully by the U.S. military to date, many development and operational challenges remain for these to become viable alternatives for manned aircraft. Aircraft engine testing: the test tig developer Engineers at Belcan's Advanced Engineering & Technology Division share their insights and experiences on the development of aircraft gas turbine test rigs and stands. This is the first installment of a three-part series on aircraft engine testing. Looking back at factory automation The ability to improve quality while substantially reducing the cost of production and span times is becoming a necessity to complete in today's aerospace industry.

Cabin window design The expanded operating conditions of the Gulfstream V aircraft required engineers to redesign the cabin window to provide for a longer service life, lighter weight, and improved functionality. European wind tunnels This first in a two-part series on global wind tunnel use and capabilities investigates several European research organizations' facilities.

Noise and vibrations control A variety of active and passive methods can be used to reduce cabin noise and fuselage vibration. Bringing efficiency to flight testing To meet itsgoal of one new aircraft activity each year, Bombardier's Flight Test Center has sought to reduce aircraft development cycle time by focusing on test planning, safety, and configuration control. Propulsion flight testing Originally conceived for just the GE90 aircraft engine program, GE Aircraft Engines' Boeing 747 flying test bed has evolved into the company's primary commercial engine test aircraft. Top technologies for 2000 Each month, "Aerospace Engineering" publishes the latest technologies. The "Aerospace Engineering" editors have reviewed thousands of reader responses during the past year and have chosen the "best of the best" along with runners-up.

Eurofighter ergonomics BAE Systems looks to Direct Voice Input to address cockpit ergonomic concerns for the Eurofighter Typhoon. Aeropropulsion testing One of the nation's largest complex of test facilities, the Arnold Engineering Development Center is involved extensively in the ground testing of propulsion systems.

Standards take flight Commercial aerospace specifications continue to gain ground as aircraft get more electric. AeroTech: A 'community of practice' 'Something for everybody' is what this SAE conference, hosted by Northrop Grumman, offers aerospace industry engineers and executives. Making flight tests more productive Simulation, testing reduce the size and number of in-flight problems.

Estimates of hypersonic aerodynamic parameters are currently uncertain due to the inadequacy of aerodynamic theories and wind tunnel techniques in the presence of molecular dissociation of the air, viscous effects, separation and surface catalysis.

This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.

AERHET results also are shown to agree approximately with the more rigorous calculations of a parabolized Navier Stokes computer program on a blunt cone configuration at angle of attack for a typical hypersonic flight condition.

A balanced program involving both the National Aeronautics and Space Administration (NASA) and industry has been structured to carry out a Supersonic Laminar Flow Control (SLFC) program. The program utilizes a balanced mix of computational efforts, ground facility experiments, and flight testing. Advanced Computational Fluid Dynamic (CFD) methods and boundary-layer stability codes offer the opportunity to analyze flow phenomena to a greater level of accuracy than in the past, yet the computational prediction and design tools need considerable development and validation for the highly three-dimensional supersonic flow conditions of the F-16XL and the High Speed Civil Transport (HSCT). Swept-wing model experiments are underway in a low-disturbance supersonic tunnel to provide data on leading-edge transition physics and flow mechanisms. On-going F-16XL-1 flight tests are obtaining laminar-flow data that will reduce the risk for the NASA experiment on the F-16XL-2.

Helicopter manufacturer and Textron Inc. subsidiary, Bell Flight, is adding a new piece of standard equipment to its Bell 407GXi single-engine, civil utility helicopter program: bird-deterring, pulsing lights.

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.

The AS2 from Aerion in Reno, Nevada, will be the first supersonic business jet to market, Boeing officials in Chicago predict. Boeing (NYSE:BA) is providing engineering, industrial, and financial resources in partnership with Aerion to accelerate technology development and aircraft design, with the goal of bringing supersonic air travel to new markets.

Boeing and SparkCognition are collaborating on unmanned aircraft system (UAS) traffic management (UTM) solutions that leverage artificial intelligence (AI) and blockchain technologies to track unmanned air vehicles in flight and allocate traffic corridors and routes to ensure safe, secure transportation.

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.

In the present work, the Osher-Chakravarthy's upwind scheme with Roe's Riemann solver is applied to solve the three-dimensional, turbulent, parabolized Navier-Stokes (PNS) equations. The governing equations are discretized by a finite volume approach, and the turbulence closure for the Reynolds stress is obtained by using a algebraic turbulence model of Baldwin-Lomax. The present PNS solver can be used for marching the solution downstream from a given initial data surface and also for generating the starting solution. Along each plane in the marching direction, the resultant algebraic equation system was solved by Strongly Implicit Procedure (SIP). Application of present solver to a test problem showed that the present numerical results agree well with the experimental data and other numerical results.