Universiti Teknologi Malaysia Institutional Repository

Pressure distribution on helicopter fuselage

Aris, Anas Faiz and Ishak, Iskandar Shah and Ali, Airi and Othman, Norazila (2019) Pressure distribution on helicopter fuselage. Journal of Transport System Engineering, 6 (1). pp. 10-16. ISSN 2289–9790


Official URL: https://jtse.utm.my/index.php/jtse/article/downloa...


Modern rotorcrafts are subjected to some of the most complex flow behaviors ever encountered by the rotorcraft aerodynamicist. The objective of this research work is to investigate the pressure distribution on a helicopter fuselage in relation to the helicopter phenomenon. In this experimental work, a standard ellipsoidal helicopter fuselage model was mated to a main-rotor-hub assembly from a remote-control helicopter. The model was equipped with 28 pressure taps where the locations of the taps were predetermined by CFD analysis. The experiments were carried out in the UTM wind tunnel with a test section of 2m (width) x 1.5m (height) x 5.8m (length) with the maximum wind speed of 80 m/s. Data of pressure corresponding to the variations of helicopter’s pylon configurations and advance ratios were recorded using Electronic Pressure Scanning System. The effects of advance ratio and pylon configuration to the pressure distribution on helicopter fuselage were analysed. Findings reveal that the employment of pylon does augmenting the pressure coefficient on the rear part of the fuselage. Results also indicate the pressure distributions on the right and left sides of the fuselage are unsymmetrical indicating a very complex flow phenomenon experienced by the helicopter fuselage.

Item Type:Article
Uncontrolled Keywords:Advance ratio, helicopter fuselage, pressure characterisation, rotorcraft, wind tunnel
Subjects:T Technology > TJ Mechanical engineering and machinery
Divisions:Mechanical Engineering
ID Code:84960
Deposited By: Fazli Masari
Deposited On:29 Feb 2020 13:51
Last Modified:29 Feb 2020 13:51

Repository Staff Only: item control page