RESEARCH IN MANEUVERABILITY OF THE XH-51A COMPOUND HELICOPTER

Abstract

The report presents the results of a research program in maneuverability and rotor loads on the compound version of the rigid-rotor XH- 51A helicopter. The principal objective of this program was to evaluate the maneuvering capability in terms of envelope expansion, longitudinal and lateral control power and damping, autorotation characteristics, level flight characteristics, and hover maneuvers. The testing included the evaluation of rotor RPM and control sensitivity changes over the target airspeed-load factor envelope for both neutral and forward centers of gravity. The maximum true airspeeds attained with a forward center of gravity were 262.7 knots at 95.5 percent rotor RPM in a shallow descent at a density altitude of 7750 feet, and 223.5 knots at 91 percent rotor speed at a density altitude of 7250 feet in level flight.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1968
Accession Number
AD0675445

Entities

People

  • F. P. Lentine
  • T. H. Oglesby
  • W. P. Groth

Organizations

  • Lockheed Martin

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airfoils
  • Airframes
  • Airplanes
  • Altitude
  • Army Aviation
  • Control Systems
  • Fixed Wing Aircraft
  • Flight Speeds
  • Geometry
  • Helicopters
  • Jet Engines
  • Mach Number
  • Measurement
  • Sea Level
  • Test And Evaluation
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.