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Parametric Studies on Airfoil-Boundary Layer Ingestion Propulsion System

Central Aerohydrodynamic Institute (TsAGI), Russia-Leonid L. Teperin
Peking University, China-Mostafa E. El-Salamony
  • Journal Article
  • 01-13-01-0003
Published 2020-03-11 by SAE International in United States
From the fact that a propulsor consumes less power for a given thrust if the inlet air is slower, simulations are conducted for a propulsor imposed behind an airfoil as ideal boundary layer ingestion (BLI) propulsor to stand on the benefits of this configuration from the point of view of power and efficiency and to get a closer look on the mutual interaction between them. This interaction is quantified by the impact on three main sets of parameters, namely, power consumption, boundary layer properties, and airfoil performance. The position and size of the propulsor have great influence on the flow around the airfoil. Parametric studies are carried out to understand their influence. BLI propulsor directly affects the power saving and all of the pressure-dependent parameters, including lift and drag. For the present case, power saving reached 14.4% compared to the propeller working in freestream.
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Performance of Isolated UAV Rotors at Low Reynolds Number

Georgia Institute of Technology-Yashvardhan Tomar, Narayanan Komerath
Indian Institute of Technology-Dhwanil Shukla
  • Technical Paper
  • 2020-01-0046
Published 2020-03-10 by SAE International in United States
Vertical takeoff and landing vehicle platforms with many small rotors are gaining importance for small UAVs as well as distributed electric propulsion for larger vehicles. To predict vehicle performance, it must be possible to gauge interaction effects. These rotors operate in the less-known regime of low Reynolds number, with different blade geometry. As a first step, two identical commercial UAV rotors from a flight test program are studied in isolation, experimentally and computationally. Load measurements were performed in Georgia Tech’s 2.13 m × 2.74 m wind tunnel. Simulations were done using the RotCFD solver which uses a Navier-Stokes wake computation along with rotor-disc loads calculation using low-Reynolds number blade section data. It is found that in hover, small rotors available in the market vary noticeably in performance at low rotor speeds, the data converging at higher RPM and Reynolds number. This is indicative of the high sensitivity of low-Re rotor flows to minor geometrical differences/imperfections in the rotors. It requires proper handling in computations. CFD results show a higher deviation from the experimental thrust data…
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A Study on Mechanical Properties and Multi Response Optimization of Process Parameters for Showing Signs of Improvement Product Quality in Drilling AlSi7Cu4 Utilizing GRA in Taguchi Method

SRM Institute Of Science And Technology-Sundar Singh Sivam Sundarlingam Paramasivam, Krishnaswamy Saravanan, Durai Kumaran, Raj Rajendran
TISHIK University-Ganesh Babu Loganathan
Published 2019-10-11 by SAE International in United States
Showing and streamlining of cutting parameters are a champion among the most essential components in drilling processes. This examination displays the change of drilling procedures parameters on AlSi7Cu4 made by Gravity Die Casting and with replies in light of OA with Taughi GRA and ANOVA. The effects of alloying parts were bear on the Chemical Composition, microstructures, mechanical property, Hardness, X-Ray and S Das response is particularly analyzed. Motivations on the progression of Drilling parameters using the Taguchi strategy to obtain slightest surface Roughness (Ra), Circularity Error, Burr size and Thrust Force. Different Drilling Trails were coordinated using the L9 OA on CNC Milling machine. The examinations were accomplished on AlSi7Cu4 composite piece cutting tool of an ISO 460.1-1140-034A0-XM GC3 of 12 mm measurement with Tool 140 degrees, used all through the preliminary work under dry cutting conditions. The central and participation effect of the data factors on the foreseen responses are analyzed. The foreseen regards and estimated regards are really close. The given system could be utilized to pick the level of infiltrating constraints.…
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BEARING, BALL, AIRFRAME, ANTIFRICTION, INTERMEDIATE DUTY

ACBG Rolling Element Bearing Committee
  • Aerospace Standard
  • AS27649E
  • Current
Published 2019-07-09 by SAE International in United States
No Abstract Available.
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Numerical Simulation of Aircraft and Variable-Pitch Propeller Icing with Explicit Coupling

ANSYS Inc.-Isik Ozcer, Guido S. Baruzzi, Miraj Desai, Maged Yassin
Published 2019-06-10 by SAE International in United States
A 3D CFD methodology is presented to simulate ice build-up on propeller blades exposed to known icing conditions in flight, with automatic blade pitch variation at constant RPM to maintain the desired thrust. One blade of a six-blade propeller and a 70-passenger twin-engine turboprop are analyzed as stand-alone components in a multi-shot quasi-steady icing simulation. The thrust that must be generated by the propellers is obtained from the drag computed on the aircraft. The flight conditions are typical for a 70-passenger twin-engine turboprop in a holding pattern in Appendix C icing conditions: 190 kts at an altitude of 6,000 ft. The rotation rate remains constant at 850 rpm, a typical operating condition for this flight envelope. Two icing conditions are simulated: air static temperature -23 °C, LWC 0.2 g/m3 and MVD 20 microns resulting in rime ice, and air static temperature -16 °C, LWC 0.3 g/m3 and MVD 20 microns resulting in mixed ice with rime to glaze transition in the radial direction. The ice shapes in both conditions are assumed to remain intact and…
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MUSIC-haic: 3D Multidisciplinary Tools for the Simulation of In-Flight Icing due to High Altitude Ice Crystals

SAE International Journal of Advances and Current Practices in Mobility

Darmstadt University of Technology-Ilia Roisman, Cameron Tropea
General Electric Aviation-Paolo Vanacore
  • Journal Article
  • 2019-01-1962
Published 2019-06-10 by SAE International in United States
Icing is a major hazard for aviation safety. Over the last decades an additional risk has been identified when flying in clouds with high concentrations of ice-crystals where ice accretion may occur on warm parts of the engine core, resulting in engine incidents such as loss of engine thrust, strong vibrations, blade damage, or even the inability to restart engines. Performing physical engine tests in icing wind tunnels is extremely challenging, therefore, the need for numerical simulation tools able to accurately predict ICI (Ice Crystal Icing) is urgent and paramount for the aeronautics industry, especially regarding the development of new generation engines (UHBR = Ultra High Bypass Ratio, CROR = Counter rotating Open Rotor, ATP = Advanced Turboprop) for which analysis methods largely based on previous engines experience may be less and less applicable. The European research project MUSIC-haic has been conceived to fill this gap and has started in September 2018. MUSIC-haic brings together the main European research institutions working on icing modelling as well as engine manufacturers and aircraft manufacturers. The project will…
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Lightweighting in Aerospace Component and System Design

  • Magazine Article
  • TBMG-33914
Published 2019-03-01 by Tech Briefs Media Group in United States

Lightweighting design is an extensively explored and utilized concept in many industries, especially in aerospace applications, and is associated with the green aviation concept. The contribution of aviation to global warming phenomena and environmental pollution has led to ongoing efforts for the reduction of aviation emissions. Approaches to achieve this target include increasing energy efficiency. An effective way to increase energy efficiency and reduce fuel consumption is reducing the mass of aircraft, as a lower mass requires less lift force and thrust during flight. For example, for the Boeing 787, a 20% weight savings resulted in 10 to 12% improvement in fuel efficiency. In addition to reduction of carbon footprint, flight performance improvements such as better acceleration, higher structural strength and stiffness, and better safety performance could also be achieved by lightweight design.

CHEBY Toolkit for Processing and Editing Chebyshev Files

  • Magazine Article
  • TBMG-33679
Published 2019-02-01 by Tech Briefs Media Group in United States

This software fits trajectory ephemerides and thrust profiles with a Chebyshev polynomial representation, and stores this fit in data files suitable for upload to a spacecraft. In addition, a number of utility modules are provided to assist with inspection and diagnosis of issues with data products. The software produces the various data products that are specific to onboard spacecraft navigation and control.

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Screw Threads, Metric Buttress - MJB Profile

E-25 General Standards for Aerospace and Propulsion Systems
  • Aerospace Standard
  • MA1696B
  • Current
Published 2019-01-03 by SAE International in United States
This standard establishes the basic triangular profile for the MJB thread form, the design profiles, standard pitches, tolerance classes, formulae for tolerances and dimensions, tolerance tables, and a system of designations. Because of the specialized application for buttress threads, no preferred diameter-pitch series have been established for this standard and each application will require use of the thread formulae for dimensions and related tolerances given herein for deriving the thread dimensional requirements.
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Vertical Take Off and Landing (VTOL) Aircraft with Vectored Thrust for Control and Continuously Variable Pitch Attitude in Hover

  • Magazine Article
  • TBMG-33584
Published 2019-01-01 by Tech Briefs Media Group in United States

Most fixed-wing VTOL unmanned aerial vehicles (UAVs) take off vertically, then transition to horizontal flight. This is a new type of UAV that has unique capability. It can vary its hover position from “nose up” (tailsitter) to “nose forward” (non-tailsitter) incrementally and continuously, and even hold a position at any angle in between.