UH-2 HELICOPTER HIGH-SPEED FLIGHT RESEARCH PROGRAM UTILIZING JET THRUST AUGMENTATION

Abstract

The results of a flight research program conducted to determine the behavior of a fully articulated, servo-flap controlled rotor system at various power levels in highspeed flight are presented. The research aircraft, instrumentation, and test program are described. A standard Kaman UH-2 helicopter was modified by the addition of a General Electric YJ-85 jet engine, without afterburner, mounted on the right side of the fuselage for horizontal thrust augmentation. Research flights were conducted up to a level-flight true airspeed of 188 knots. Airspeeds limited by retreating blade stall or advancing blade compressibility were established. The effects of density altitude, rotor speed and power, tip speed ratio, thrust augmentation and aircraft gross weight on the limit airspeeds are discussed. It is concluded that the speed envelope for rotary wing aircraft can be substantially expanded by unloading the main rotor through the application of horizontal thrust augmentation.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1965
Accession Number
AD0616104

Entities

People

  • A. A. Whitfield
  • W. E. Blackburn

Organizations

  • Kaman Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Autorotation
  • Center Of Gravity
  • Contracts
  • Control Systems
  • Flight Speeds
  • Helicopters
  • Instrument Panels
  • Mach Number
  • Pilot Seats
  • Power Levels
  • Propulsion Systems
  • Research Aircraft
  • Rotary Wing Aircraft
  • Standards
  • Structural Loads

Readers

  • Aerospace Engineering