The experimental study of the effect of bias flow on aerodynamic forces of nacelle d-chamber
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Date
2017-06
Authors
Mohammad Amir Izuddin Ishak
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Abstract
The ice protection system and bias liner is an integrated concept that could be used to provide both aircraft ice protection and noise abatement. Current aircraft uses a Piccolo Tube Anti-Icing system which impinges jets of hot air for ice protection. The bias liner is an acoustic liner which allows air to flow through each of the cells and act as sound abatement device. If the hot air is dumped overboard via these cells, it can function as a bias flow. The effect of bias flow towards the aerodynamic performance of nacelle Dchamber is studied. An investigation was carried out by using two developed models of nacelle D-chamber; one solid model and one modified bias model. The modified model is having a perforated skin with single row of porous holes at the bottom part. The bias flow supply was positively quantified by the internal pressure difference of the nacelle D-chamber with the ambient, up to 160 Pa ranging from 10-20 m/s free stream velocities. According to the experimental study, bias flow does provide a promising result. The flow helps in reducing drag coefficient and enhance the lift coefficient of the nacelle D-chamber. The experiment also found that critical pressure of drag reduction is 60 Pa and the percentage of difference for lift coefficient and drag coefficient are independent with free stream velocity.