16H-1A FLIGHT TEST RESEARCH PROGRAM

Abstract

The report presents the results of a flight test program on the Piasecki Model 16H-1A shaft-driven compound helicopter. The main components of the Model 16H-1A aircraft included: an H-21 articulated rotor, a wing with controllable flaperons and a shrouded pusher propeller. The aircraft was powered by a single T58-8 turbine engine. Aircraft performance, flying qualities, vibration and lift distribution between main rotor and wing were investigated over a level flight speed range of 0 to 167 knots and dive speeds up to 195 knots.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1968
Accession Number
AD0675443

Entities

People

  • D. N. Meyers
  • J. H. Goldberg
  • L. V. Tompkins

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Control Systems
  • Dynamic Response
  • Engineers
  • Fixed Wing Aircraft
  • Flight Speeds
  • Fuselages
  • Horizontal Stabilizers
  • Landing Gear
  • Measurement
  • Rotary Wing Aircraft
  • Sea Level
  • Spars

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering