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System integration in aircraft environment – Hydraulic performances through coupled simulations

Airbus Operations GmbH-Henning Witt lng
Airbus Operations India-Ashutosh Singh
  • Technical Paper
  • 2020-01-0004
To be published on 2020-03-10 by SAE International in United States
An Airbus methodology for the assessment of accurate hydraulic performance at early program stages in the complete aircraft and power consuming systems environment based on joint collaboration with Chiastek is presented. The aim is to comfort the prediction of an aircraft hydraulic performance in order to limit the need for a physical integration test bench and extensive flight test campaign but also to avoid late system redesign based on robust early stage model based engineering and to secure the aircraft entry-into-service
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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
To be published on 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 geomety. 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 2.13m x 2.74m wind tunnel. Simulations were done using the RotCFD solver which uses a Navier-Stokes wake computation with 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 may be 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 at low rotor speeds. While thrust…
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Using Engine Test Data to Model Engine Performance

S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
  • Aerospace Standard
  • AIR5509A
  • Current
Published 2019-11-05 by SAE International in United States
This document defines the process steps involved in collecting and processing engine test data for use in understanding engine behavior. It describes the use of an aero-thermal cycle model for reduction and analysis of those data. The analysis process may include the calculation of modifiers to match the model to measured data and prediction of engine performance based on that analysis.
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Method for Predicting Lateral Attenuation of Airplane Noise

A-21 Aircraft Noise Measurement Aviation Emission Modeling
  • Aerospace Standard
  • AIR5662
  • Current
Published 2019-10-04 by SAE International in United States
This document describes analytical methods for calculating the attenuation of the level of the sound propagating from an airplane to locations on the ground and to the side of the flight path of an airplane during ground roll, climbout after liftoff, and landing operations. Both level and non-level ground scenarios may be modeled using these methods, however application is only directly applicable to terrain without significant undulations, which may cause multiple reflections and/or multiple shielding effects. This attenuation is termed lateral attenuation and is in excess of the attenuation from wave divergence and atmospheric absorption. The methods for calculating the lateral attenuation of the sound apply to: turbofan-powered transport-category airplanes with engines mounted at the rear of the fuselage (on the sides of the fuselage or in the center of the fuselage as well as on the sides) or under the wings propeller-driven transport-category or general-aviation airplanes propagation over ground surfaces that may be considered to be “acoustically soft” such as lawn or field grass situations where the terrain to the sides of the flight…
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The Cloud Detectability Conundrum

Collins Aerospace-Darren Glenn Jackson
Published 2019-06-10 by SAE International in United States
Since the beginning of aviation, aircraft designers, researchers, and pilots have monitored the skies looking for clouds to determine when and where to fly as well as when to deice aircraft surfaces. Seeing a cloud has generally consisted of looking for a white / grey puffy orb floating in the sky, indicating the presence of moisture. A simple monitoring of a temperature gauge or dew point sensor was used to help determine if precipitation was likely or accumulation of ice / snow on the airframe could occur.Various instruments have been introduced over the years to identify the presence of clouds and characterize them for the purposes of air traffic control weather awareness, icing flight test measurements, and production aircraft ice detection. These instruments have included oil slides, illuminated rods, vibrating probes, hot wires, LIDAR, RADAR, and several other measurement techniques. Each technology has its own strength and weakness including the particle size range and water content that can be measured and its ability (or lack thereof) to discriminate different types of icing conditions.The FAA release…
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SLD and Ice Crystal Discrimination with the Optical Ice Detector

Collins Aerospace-Kaare J. Anderson, Mark D. Ray
Published 2019-06-10 by SAE International in United States
In response to new safety regulations regarding aircraft icing, Collins Aerospace has developed and tested an Optical Ice Detector (OID) capable of discriminating among icing conditions appropriate to Appendix C and Appendix O of 14 CFR Part 25 and Appendix D of Part 33. The OID is a short-range, polarimetric lidar that samples the airstream up to ten meters beyond the skin of the aircraft. The intensity and extinction of the backscatter light correlate with bulk properties of the cloud, such as water content and phase. Backscatter scintillation (combined with the outside air temperature from another probe) signals the presence of supercooled large droplets (SLD) within the cloud-a capability incorporated into the OID to meet the requirements of Appendix O.Recent laboratory and flight tests of the Optical Ice Detector have confirmed the efficacy of the OID to discriminate among the various icing conditions. Drizzle-sized droplets, mixed with a small droplet cloud in the Collins Cloud Chamber, appear as scintillations in the lidar signal when it is processed pulse-by-pulse. Averaging the signal over multiple pulses, causes…
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On-Ground Cold Soak Fuel Frost Modeling

Embraer-Daniel Martins da Silva, Luis Santos, André Katchborian, Rodrigo Sousa
Published 2019-06-10 by SAE International in United States
In this paper a cold soak fuel frost modeling for an aircraft wing tank is presented. Numerical prediction is compared with experimental data and a qualitative verification for the frost formation and melting is also shown. The numerical simulation showed good agreement with experimental observations. The model was used to define, through a Monte Carlo analysis, two different frost formations whose impact on aircraft handling was evaluated by flight tests using representative grits.
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Wind Tunnel Measurements of Simulated Glaciated Cloud Conditions to Evaluate Newly Developed 2D Imaging Probes

Artium Technologies Inc.-William D. Bachalo
CIRA, Italian Aerospace Research Centre-Biagio M. Esposito
Published 2019-06-10 by SAE International in United States
Instrumentation that has been used for characterization of mixed-phase and glaciated conditions in the past, like the OAP probes, are subject to errors caused by variations in diffraction on the images away from the object plane and by the discrete nature of their particle detection and sizing. Correction methods are necessary to consider their measurements adequate for high ice water content (IWC) environments judged to represent a significant safety hazard to propellers and turbofan engine operability and performance. For this reason, within the frame of EU FP7 HAIC project, instrumentation characterization and validation is considered a major element need for successful execution of flight tests campaigns. Clearly, instrumentation must be sufficiently reliable to assess the reproducibility of artificial clouds with high ice water content generated in icing tunnels. Instruments are required to measure these conditions with a sufficient level of accuracy for the purposes of the testing. Currently, there is an anticipated basic uncertainty of a factor of 2-5 when measuring clouds in-situ. This may be worse for thunderstorm core regions, because of the poorly…
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Korean Utility Helicopter KUH-1 Icing Certification Program

Korea Aerospace Industries (KAI)-Yoo Sang Hwang, Jik Soo Kim, Kyung Sam Kim
Netherlands Aerospace Centre (NLR)-Stefan van 't Hoff, Karel Lammers
Published 2019-06-10 by SAE International in United States
The KUH-1 Surion is a twin-engine utility helicopter designed and developed jointly by Korea Aerospace Industries (KAI) and Airbus Helicopters primarily for the Republic of Korea Army (ROKA). Following customer requirements, KAI launched a program aimed at the military qualification of the KUH-1 for flight in icing conditions following tailored airworthiness certification criteria based on 14 CFR Part 29 and DEF STAN 00-970. The Netherlands Aerospace Centre (NLR) became involved in the program on the eve of the first icing flight test campaign performed in the winter of 2015/2016. NLR has supported all subsequent test activities and the finding of compliance in close collaboration with KAI and certain suppliers. The test activities performed include 1) component-level development and qualification icing wind tunnel testing at Cox & Co in Long Island, NY, 2) icing qualification testing of the engine air intake ice protection system at Rail Tec Arsenal (RTA) in Vienna, Austria, 3) artificial icing flight testing using the US Army Helicopter Icing Spray System (HISS), and 4) natural icing flight testing of the complete aircraft…
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CH148 Icing Flight Test Performance Data Correlation

Sikorsky, a Lockheed Martin Company-Daniel Griffiths
Published 2019-06-10 by SAE International in United States
This paper presents results of correlation of an empirical code to CH148 Cyclone® icing flight test performance data. Predicted icing main rotor torque penalties, generated using the Sikorsky Generalized Rotor Performance (GRP) model with the integral DELICE icing performance module, are compared to flight test results. DELICE methodology adjustments are shown that lead to CH148 test data correlation and improved correlation to previously-examined S-92A™ icing flight test performance data. Finally, a comparison of results between GRP and Sikorsky-Maryland FreeWake is shown, providing an indication of the influence of rotor wake methodology on icing model correlation.
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