Hostname: page-component-586b7cd67f-rdxmf Total loading time: 0 Render date: 2024-11-27T22:16:41.493Z Has data issue: false hasContentIssue false
  • English
  • Français

Investigation of the aerodynamic performance and noise characteristics of a 1/5th scale model of the Dowty Rotol R212 propeller

Published online by Cambridge University Press:  04 July 2016

W. J. G. Trebble
Get access Rights & Permissions [Opens in a new window]

Summary

An investigation of the four-bladed Dowty Rotol R212 propeller (NACA 16 sections) has been made at l/5th scale (0·7 metre diameter) in the RAE 1·5 metre acoustic tunnel. Propeller power absorption and thrust have been measured over a range of rotational speeds up to 8000 rev/min at mainstream speeds from 15 m/s to 60 m/s for a range of blade settings. Slipstream wake surveys show outward movement of the position of the peak pressure as propeller loading is increased.

Noise analysis demonstrates the predominance of multiple tones whose number and intensity increase with helical-tip Mach number. An empirical formula shows that the fundamental tone SPL varies with tip speed and power loading in an identical manner to that observed on a modern ARA-D section propeller.

Type
Research Article
Information
The Aeronautical Journal , Volume 91 , Issue 905 , May 1987 , pp. 225 - 236
Copyright
Copyright © Royal Aeronautical Society 1987 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Trebble, W. J. G., Williams, J. and Donnelly, R. P. Comparative acoustic wind-tunnel measurements and theoretical correlations on subsonic aircraft propellers at full-scale and model-scale. AIAA-81-2004, RAE Technical Memorandum Aero 1909, 1981.Google Scholar
2. Trebble, W. J. G. Investigation of effects of blade tip shape on aerodynamic performance and noise characteristics of a 0·7 metre diameter propeller. RAE Technical Memorandum Aero 1974, 1983.Google Scholar