Transonic Pressure Distribution on an Aircraft Wing Model during Rocket Sled Runs.

Abstract

Hardware and techniques are described which were used in a series of rocket sled runs aimed at measuring aerodynamic data in the transonic speed regime during rocket sled runs. During these tests surface pressure distribution was measured on an aircraft wing model mounted in vertical position on a rocket sled at Mach numbers between zero and Mach 0.95 and at Reynolds numbers (based on cord length) up to 23 millions. The data were collected while sweeping the entire Mach number range both during acceleration and during deceleration. Selected data obtained in this test series are presented and compared with wind tunnel and flight test results. The influence of time delay in the pressure tubing is discussed and methods for compensating for this effect are presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1977
Accession Number
ADA041633

Entities

People

  • Hans J. Rasmussen

Organizations

  • Air Armament Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Acquisition
  • Aerodynamic Characteristics
  • Aircrafts
  • Boundary Layer
  • Data Acquisition
  • Flow Visualization
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Rocket Sleds
  • Test And Evaluation
  • Test Methods
  • Vibration
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Inertial Navigation Systems.