McCluer_AHS02 - Full-Span Tiltrotor Aeroacoustic Model (FS...

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Full-Span Tiltrotor Aeroacoustic Model (FS TRAM) Overview and Initial Testing Megan S. McCluer NASA Ames Research Center Moffett Field, CA Jeffrey L. Johnson Aerospace Computing, Inc. Mountain View, CA ABSTRACT The Full-Span Tiltrotor Aeroacoustic Model (FS TRAM) is a dual-rotor, powered wind tunnel model with extensive instrumentation for measurement of structural and aerodynamic loads. The model has been developed to investigate tiltrotor aeromechanics and to generate a comprehensive database for validating analyses, as well as a research platform for studying current and future tiltrotor designs. This paper describes the Full-Span TRAM test stand and the first set of data obtained at the NASA Ames Research Center 40- by 80-Foot Wind Tunnel test conducted in late 2000. Limited results are presented and recommendations for future testing are provided. This model has been established as a valuable national asset for tiltrotor research. INTRODUCTION The tiltrotor is a versatile aircraft which can fly with the speed and range of a turboprop airplane while also having the vertical take-off and landing capability of a helicopter. Wind tunnel testing of tiltrotor models increases the understanding of tiltrotor aerodynamics, dynamics, performance, and acoustics, and enables the development of advanced computational design tools. Wind tunnel data can also be used to improve simulation models and investigate detailed conditions that are too arduous to obtain in flight test. The Full-Span Tilt Rotor Aeroacoustic Model (FS TRAM), shown in Figure 1, is a 1/4-scale representation of the V-22 Osprey aircraft (Figure 2) and was tested at the NASA Ames Research Center 40- by 80-Foot Wind Tunnel in late 2000. The first full-span test served primarily as a complete system build-up and checkout. Model, motor, and rotor system controls and measurements were built, installed, and verified. Limited test data were obtained on rotor performance, blade structural loads, and wing static pressures. Some laser light sheet flow visualization images and acoustics data were also obtained. Additional testing will provide the full-span tiltrotor data the rotorcraft community requires, since isolated and semi- span model testing do not fully address all tiltrotor aeromechanics issues. The long-term goal of the FS TRAM is to be a tiltrotor research tool for future testing by the U.S. industry and Government. Presented at the American Helicopter Society Aerodynamics, Acoustics, and Test and Evaluation Technical Specialists’ Meeting, San Francisco, CA, January 23-25, 2002. Copyright © 2002 by the American Helicopter Society International, Inc. All rights reserved. Figure 1. The Full-Span TRAM mounted in the NASA Ames 40- by 80-Foot Wind Tunnel. Figure 2. The V-22 Osprey tiltrotor aircraft during shipboard operational evaluations. (U.S. Navy Photo)
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Full-Span TRAM Overview and Initial Testing Page 2 of 17 Prior to the complete full-span model construction, the right rotor and nacelle were tested in the Duits- Nederlandse Windtunnel (DNW) in 1998. The purpose
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McCluer_AHS02 - Full-Span Tiltrotor Aeroacoustic Model (FS...

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