Experimental View on Performance of Flow Past Over A Symmetrical Aerofoil at Low Subsonic Speed

Published in Journal

Anusandhan (RNTUJ-AN) [RNTUJ-AN] (Vol:17/ Issue: 26) DOI: [NA]
Authors: Amit Kumar* Vinay Yadav
Subjects: Technology & Management

Year: March, 2015
Volume: 17 / Issue: 26
Pages: 694-669
Publisher: RNTU
Source:
ISSN: 2278-4187
E-ISSN: 2457-0656
DOI: NA
Published URL:
Published On: March, 2015

Article Details

Experimental View on Performance of Flow Past Over A Symmetrical Aerofoil at Low Subsonic Speed | Original Article

Amit Kumar* Vinay Yadav in Anusandhan (RNTUJ-AN) | Multidisciplinary Academic Research

ABSTRACT:

This paper brings us the aero dynamics properties of flow over symmetrical aerofoil (NACA-0012) at low subsonic speed (M<0.3). Generally symmetrical aerofoil are used in supersonic aircraft for military purpose like fighter and bomber to give smooth speed at supersonic speed (M>1) and including compressible effect. Here attempt has been made to determine pressure distribution over symmetrical aerofoil at low sub-sonic speed and in viscid incompressible flow. The flow behavior on symmetrical aerofoil of upper and lower side has been investigated. So we get behavior of flow over a wing whose wing span and chord length is given, like we can predict about pressure distribution over any type of aerodynamics shape used in any subsonic and supersonic speed of vehicle (aircraft). Experiment were out in low subsonic open circuit wind tunnel having speed in test section is M<0.08 and theoretically analyzed for its performance.