Estimating Blade Section Airloads from Blade Leading-Edge Pressure Measurements

Abstract

The Tilt-Rotor Aeroacoustic Model (TRAM) test in the Duitse-Nederlandse Wind (DNW) Tunnel acquired blade pressure data for forward flight test conditions of a tiltrotor in helicopter mode. Chordwise pressure data at seven radial locations were integrated to obtain the blade section normal force. The present investigation evaluates the use of linear regression analysis and of neural networks in estimating the blade section normal force coefficient from a limited number of blade leading-edge pressure measurements and representative operating conditions. These network models are subsequently used to estimate the airloads at intermediate radial locations where only blade pressure measurements at the 3.5% chordwise stations are available.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 2003
Accession Number
ADA480503

Entities

People

  • Johannes M. Van Aken

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Airframes
  • Databases
  • Graphical User Interface
  • Helicopters
  • Information Science
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Measurement
  • Neural Networks
  • Pressure Measurement
  • Pressure Transducers
  • Regression Analysis
  • Tilt Rotor Aircraft
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • AI & ML
  • AI & ML - Bayesian Inference
  • AI & ML - Neural Networks