Wind tunnel investigations of aircraft airfoil in cruise conditions

Abstract

Presented work is focused on analysis of the flow over the 2D model of Airbus A320 airfoil wing in cruise phase of the flight. For this purpose the measurement channel with an airfoil model was designed and assembled in a transonic wind tunnel to obtain a similar flow pattern as in the reference two-dimensional freestream flow. Experimental investigations were conducted in the IMP PAN transonic wind tunnel with a relative narrow test section which is a novel approach in terms of these type of research. The test section was designed using CFD simulations based on 2D freestream flow for the tested wing profile and in the next step the research were continued experimentally in transonic wind tunnel with a measurement chamber width of 100 mm. This paper presents the results of reference investigations on the A320 wing profile which combines experimental tests and CFD calculations. The obtained results show that the approach presented in the paper is appropriate and the obtained flow features in the tunnel do not differ much from the freestream conditions.

Optical fibre pressure sensing using a frequency modulated laser-based signal processing technique

“…The FP pressure sensor was installed in a Necuron block along with a commercial electronic pressure transducer, Kulite XCS-093, to allow the benchmarking of the optical measurements. The Kulite pressure transducer was chosen since it is widely used in wind tunnel tests for aerospace applications [35][36][37]. The device operates via the use of a fully active, four arm Wheastone bridge that is temperature compensated for operation between −55 • C and 120 • C, and possesses a maximum combined non-linearity and hysteresis of 0.5% of full-scale [38].…”

B‐spline based on vector extension improved CST parameterization algorithm

“…A good parameterization methodology should have the following features-firstly, it should have a large optimization space; secondly, it has good local control ability and a relatively small number of design variables; finally, it needs to be ensured that the geometric shape of the aircraft in the optimization process is smooth. [20][21][22][23][24] The shape design of the aircraft is also a crucial step in the aerodynamic optimization of the aircraft that determines the overall aerodynamic performance of the aircraft. Hence the first step of the shape design of the aircraft is to employ a proper parameterization method to generate a basic aircraft shape.…”

“…The first step of the shape design of the aircraft is to parameterize the shape, which has a critical influence on the success of the aircraft design and directly affects the overall project progress. A good parameterization methodology should have the following features—firstly, it should have a large optimization space; secondly, it has good local control ability and a relatively small number of design variables; finally, it needs to be ensured that the geometric shape of the aircraft in the optimization process is smooth 20‐24 . The shape design of the aircraft is also a crucial step in the aerodynamic optimization of the aircraft that determines the overall aerodynamic performance of the aircraft.…”