EXPLORATION OF HIGH-SPEED FLIGHT WITH THE XH-51A RIGID ROTOR HELICOPTER

Abstract

A systematic research program to investigate the capability of the Lockheed-developed 'rigid' rotor system in the XH-51A helicopters is discussed. The primary objective of the research program was to attain level flight performance at a true airspeed of 200 knots; 210 knots true airspeed was actually attained with the Compound XH-51A. Analytical studies, design, fabrication and modification, laboratory tests, wind tunnel and ground tests, and research flight tests of two rotor configurations and a 'compound' version of the helicopter were performed.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1965
Accession Number
AD0617966

Entities

People

  • William K. Foulke

Organizations

  • Lockheed Martin

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airfoils
  • Airframes
  • Bending Moments
  • Design Criteria
  • Fatigue Tests (Mechanics)
  • Flight Speeds
  • Fuselages
  • Helicopters
  • Horizontal Stabilizers
  • Mach Number
  • Measurement
  • Sea Level
  • Test And Evaluation
  • Wind Tunnel Tests

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Systems Analysis and Design