Analytical Calculations of Helicopter Torque Coefficient (CQ) and Thrust Coefficient (CT) Values for the Helicopter Performance (HELPE) Model.

Abstract

A computer program for calculating helicopter torque coefficients (CQ) and thrust coefficients (CT) as a function of a vehicle's forward speed has been developed in conjunction with the helicopter performance assessment project. The model is based on the energy principle, in which helicopter power is broken into three components: induced power, profile power, and parasite power. This report documents the basic mathematical model used in the code, along with the numerical solution scheme used in implementing the model. Results are calculated for the UH-60A Black Hawk helicopter for hover and different forward speed settings and correlated with existing flight test data. The effects of different disk loading on helicopter power requirements are also investigated. The present model agrees reasonably well with the flight test data, providing the author with a certain confidence in the helicopter aerodynamic model developed in the present study.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1999
Accession Number
ADA365512

Entities

People

  • Ki C. Kim

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Equations
  • Flight
  • Fluid Dynamics
  • Helicopters
  • Mach Number
  • Military Research
  • Rotary Wing Aircraft
  • Tail Rotors
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)