Flight Tests of the Sikorsky HNS-1 (Army YR-4B) Helicopter. 1 - Experimental Data on Level-Flight Performance with Original Rotor Blades

Abstract

Level flight performance measurements were made on the TR-4B helicopter with the original set of main-rotor blades and a gross weight of approximately 2560 pounds. The minimum shaft power required by the main rotor at cruising rpm (225 rotor rpm, 2100 engine rpm) was approximately 99 hp at a speed of 40 mph. The shaft power absorbed by the tail rotor at cruising rpm was approximately 3 to 4 hp over a range of speeds from 25 to 80 mph.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1945
Accession Number
ADA801491

Entities

People

  • F. B. Gustafson

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airframes
  • Airspeed
  • Center Of Gravity
  • Coefficients
  • Experimental Data
  • Flight
  • Fuselages
  • Helicopters
  • Horsepower
  • Level Flight
  • Measurement
  • Parasites
  • Rotary Wing Aircraft
  • Tail Rotors

Fields of Study

  • Physics

Readers

  • Aerospace Engineering