Data Reduction for the Unsteady Aerodynamics on a Circulation Control Airfoil.

Abstract

Calculating the lift, drag, and pitching moment coefficients for an airfoil from the static pressure distribution obtained from wind tunnel tests is routine task when steady flow is considered, but it is much more complicated when the airfoil is operating in an unsteady flow field, similar to that experienced by a helicopter rotor blade, produced by an oscillating wind tunnel. A data reduction routine capable of condensing the large numbers of data associated with the unsteady investigation, as well as a numerical integration algorithm for the unsteady aerodynamic coefficients, were developed; however, no unsteady data were collected due to hardware failures. The ability of the program was demonstrated on previously obtained steady and quasi-steady data and sample results were presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1977
Accession Number
ADA041153

Entities

People

  • Billy Murel Pickelsimer

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Acquisition
  • Computer Programs
  • Computers
  • Data Acquisition
  • Data Processing
  • Data Reduction
  • Dynamic Pressure
  • Flow
  • Instrumentation
  • Numerical Integration
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Steady Flow
  • Unsteady Aerodynamics
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Instructional Design and Training Evaluation.