Engineering Flight Test of the OH-6A Helicopter (Cayuse). Phase D

Abstract

Performance and stability and control tests were conducted on the OH- 6A helicopter to determine compliance with the detail specification HTC-AD 369- Y-8003 and to provide information for the operator's manual. The testing was conducted at Edwards Air Force Base, California and at auxiliary test sites at Bakersfield and Bishop, California. The OH-6A met all performance guarantees except for the OGE Standard Day, 2613 pound gross weight, sea level hover guarantee. For this condition the hover height was 15 feet. The overall stability and control characteristics were considered satisfactory and complied with the requirements of military specification 8501-A with the allowed deviations in the detail specification with the exception of the maximum roll rate allowed in paragraph 3.3.15, which was exceeded but was satisfactory.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1969
Accession Number
AD0855043

Entities

People

  • John I. Nagata
  • John J. Shapley Jr.

Organizations

  • Edwards Air Force Base

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Altitude
  • Control Systems
  • Flight Control Systems
  • Fuel Systems
  • Helicopters
  • Instrumentation
  • Level Flight
  • Rotary Wing Aircraft
  • Sea Level
  • Tail Rotors
  • Test And Evaluation
  • Turbines

Readers

  • Aerospace Engineering