ANALYTICAL STUDY OF AIR DATA EQUATIONS FOR A HEMISPHERICAL PRESSURE PROBE THROUGH THE HYPERSONIC MACH NUMBER RANGE

Abstract

Air data outputs obtainable from pressure measurements on a hemispherical probe were investigated analytically for Mach numbers of 0 to 20 and altitudes from 0 to 300,000 feet. Angles of attack from +50 deg to -20 deg and angles of sideslip up to + and - 15 deg are considered using a five orifice probe. Emphasis was placed on the hypersonic regime wherein air data parameters were shown to be obtainable by using a simplified set of pressure relations. Expressions for determining the uncertainties in the air data outputs resulting from both pressure measurement error and simplifying assumptions used in deriving the air data equations are presented. Errors resulting from changes in probe shape due to ablation are also considered. Finally, limitations in deriving air data information with this approach are presented.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1967
Accession Number
AD0821818

Entities

People

  • David J. Romeo

Organizations

  • Calspan

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Altitude
  • Dynamic Pressure
  • Flight
  • Flow
  • Hypersonic Flow
  • Mach Number
  • Materials
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Stagnation Point
  • Stagnation Pressure
  • Standards
  • Static Pressure
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow