An Experimental/Theoretical Correlation of Model and Full-Scale Rotor Performance at High Advancing-Tip Mach Numbers and High Advance Ratios

Abstract

Aerodynamic performance of two reduced-scale model rotors has recently been obtained in a Freon atmosphere in the NASA-Langley Transonic Dynamics Tunnel. The results are compared with existing full-scale wind tunnel and inflight rotor performance data to substantiate this method of testing rotors. Additionally, current state-of-the-art analytical techniques are employed to calculate the model performance. Possible implications are that a rotor tested in Freon may experience less severe stall and compressibility effects than would be shown by a corresponding rotor tested in air.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1971
Accession Number
AD0881982

Entities

People

  • Bruce D. Charles

Organizations

  • Bell Flight

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Bending Moments
  • Boundary Layer
  • Boundary Layer Flow
  • Department Of Defense
  • Government Procurement
  • Governments
  • Mach Number
  • Measurement
  • Model Tests
  • Rotary Wing Aircraft
  • Two Dimensional
  • Unsteady Aerodynamics
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.