Abstr:L1T2 3 element airfoil

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Application Area 1: External Aerodynamics

Application Challenge AC1-08

Abstract

The UK National High Lift Programme (NHLP) was a collaborative project carried out in the 1970s between DERA and BAE SYSTEMS (RAE and BAC at the time). A range of models was tested including a 3-D half model, a swept panel wing, a quasi-2D (end plate) model and a truly 2D model. A comprehensive set of well-analysed and well-understood data exist for the last of these. Measurements carried out by Moir [1] at low subsonic conditions are available for a 2D wing of supercritical aerofoil section for three different high lift device configurations. Surface pressures together with lift, drag and pitching moment (obtained by integrating surface pressures) are available. The momentum deficit in the wake was measured by a pitot-static traverse. In addition, information on boundary layer and wake development and their interactions was provided by pitot-static traverses normal to the wing at various chordwise locations. All measurements are available in the form of an AGARD dataset.

This application challenge is focussed on one of the 2D high lift configurations (The L1T2 test case). The L1T2 case is a 3 element aerofoil consisting of a main element, a slat forward of the main element (deflection angle 25^0), and a Fowler flap aft of the main element (deflection angle 20^0). See Figure 1. Measurements were made at two incidences, one at a low angle of attack and one close to maximum lift.

QinetiQ has provided computations for the L1T2 test case on a multi-block mesh using the BAE SYSTEMS RANSMB flow solver with a k-g turbulence model.

The optimal design of high lift devices for take-off and landing conditions is an important and challenging problem for the aircraft industry. Difficulties are caused by the geometrical complexity and the flow physics modelling. The flow field around a multi element aerofoil is dominated by viscous flow phenomena such as strong interactions between wakes from upstream elements with boundary layers on elements downstream, flow separation, streamline curvature effects and adverse pressure gradients. It is a challenging task for a turbulence model to predict correctly the turbulent boundary layer development, flow in the wake, and in regions where wake and boundary layer interact. Poor modelling of these regions of the flow can lead to inaccurate prediction of wing loads and inaccurate prediction of flow separation. It is crucial for a CFD method to be able to accurately model these effects and flow features in order to give useful estimates of aerodynamically relevant quantities such as maximum lift.


The DOAPs for this test case are lift/incidence and lift/drag polars, boundary layer and wake profiles, and pressures on the surface and in the wake. However, only surface pressures and total pressure profiles normal to the wing surface at four chordwise locations are compared in this document. The four chordwise locations are defined in section 2.1. The surface pressure coefficients and total pressure coefficients are defined as follows:-



C_p = {{P - P_\infty} \over {{1 \over 2} \rho_\infty Q_\infty^2}}



C_{p_\text{tot}} = {{P_\text{tot} - P_\infty} \over {{1 \over 2} \rho_\infty Q_\infty^2}}


Where \rho_\infty, P_\infty and Q_\infty are the free-stream density, pressure and speed respectively.

The total pressure is defined as:



P_\text{tot} = P{\left(1 + {1 \over 2} (\gamma - 1) M^2 \right)}^{\gamma \over {\gamma - 1}}


Where M is the Mach number and \gamma is the ratio of specific heat capacities (1.4 for air).


Contributors: Antony Hutton; Jan Vos - QinetiQ; CFS Engineering SA


Front Page

Description

Test Data

CFD Simulations

Evaluation

Best Practice Advice

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