Investigation of Dive Brakes and a Dive-Recovery Flap on a High-Aspect-Ratio Wing in the Langley 8-Foot-High-Speed Tunnel

Abstract

Tests were conducted to determine suitability of dive-control devices in limiting aircraft terminal Mach number and in obtaining favorable dive-recovery characteristics for proposed supersonic aircraft. Results show that slotted brake limits terminal Mach number to values below 0.880 for altitudes to 35,000 ft. and 80 lb. per sq. ft. wing loading. Dive recovery flap produces necessary trim changes for controlled pull-outs at 25,000 ft. for Mach number range of 0.800 -0.900. Basic changes in spanwise loading were included for evaluating wing strength requirements.

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Document Details

Document Type
Technical Report
Publication Date
Aug 28, 1946
Accession Number
ADA800549

Entities

People

  • Axel T. Mattson

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Airplanes
  • Altitude
  • Aspect Ratio
  • Control Surfaces
  • Fluid Dynamics
  • Horizontal Stabilizers
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Supersonic Aircraft
  • Surfaces
  • Terminals

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow