HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 2. PARAMETRIC DESIGN STUDY

Abstract

The parametric analysis determines the optimum design parameters of a 24,000-lb.-payload helicopter powered by turbojet engines installed at the rotor blade tips. The method used determined a gross weight which would satisfy statistical component weight equations and aerodynamic equations simultaneously. The optimizing criterion was the minimum gross weight required to perform a specific mission. The results of the analysis indicate that the optimum configuration using the Continental Model 357-1 engine is a helicopter with (a) four blades, (b) two engines per blade, and (c) a crane-type fuselage. The optimum configuration with a generalized or 'rubber' engine is a helicopter with (a) three blades, (b) one engine per blade, and (c) a crane-type fuselage.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0625819

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Configurations
  • Aircrafts
  • Airframes
  • Blade Tips
  • Engine Components
  • Engines
  • Equations
  • Fuselages
  • Gas Turbines
  • Helicopters
  • Jet Aircraft
  • Parametric Analysis
  • Resonant Frequency
  • Sea Level
  • Turbines
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Operations Research