Skip to main content

Prediction of Blade‐Vortex Interaction Noise Using Airloads Generated by a Finite‐Difference Technique

Buy Article:

$30.00 plus tax (Refund Policy)

Abstract:

A numerical finite‐difference procedure has been developed for the prediction of helicopter blade loads during realistic self‐generated three‐dimensional blade‐vortex interactions (BVI). Here, the velocity field is obtained through a nonlinear superposition of the rator flow field computed using the unsteady three‐dimensional full potential rotor flow solver RFS2.RVI and the rotational vortex flow field computed using the Law of Biot‐Savart. Potential blade‐vortex encounters are identified and tracked in time at equal increments of rotor azimuth using the lifting‐line helicopter/rotor trim code CAMRAD. Utilizing the predicted airloads from the finite‐difference full potential computations, a BVI noise prediction based on Farassat's formulation 1A was used to compute the acoustic signature of the rotor. The acoustic pressure time histories and spectral analyses for the OLS model rotor were predicted with reasonable accuracy for a range of microphone locations under different rotor operating conditions. Despite the accurate prediction of the acoustic waveforms, the peak amplitude was consistently underpredicted. However, the inclusion of RVI noise source in the acoustic analysis improved the PNLT prediction significantly. For the model OLS rotor, reasonable correlation with the experimental wind tunnel surface pressure and acoustic data was obtained.

Document Type: Research Article

DOI: http://dx.doi.org/10.4050/JAHS.37.38

Affiliations: McDonnell Douglas Helicopter Company, Mesa, Az.

Publication date: October 1, 1992

More about this publication?
  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

    Journal subscribers who are AHS members log in here if you are not already logged in.

    Authors can find submission guidelines and related information on the AHS website.

ahs/jahs/1992/00000037/00000004/art00005
dcterms_title,dcterms_description,pub_keyword
6
5
20
40
5

Access Key

Free Content
Free content
New Content
New content
Open Access Content
Open access content
Subscribed Content
Subscribed content
Free Trial Content
Free trial content
Cookie Policy
X
Cookie Policy
Ingenta Connect website makes use of cookies so as to keep track of data that you have filled in. I am Happy with this Find out more