Test Data AC1-08

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L1T2 3 element airfoil

Application Challenge 1-08 © copyright ERCOFTAC 2004

Overview of Tests

The measurements are fully described in [1]. For the purposes of this document, only the L1T2 test case will be described. The AGARD data is in the public domain and available in electronic form. These consist of lift-drag polars (i.e. lift versus drag over a range of incidences) as well as surface pressure distributions and wake traverses taken over various incidences. In addition boundary layer and wake velocity profiles were measured by pitot-static traverses at selected positions and two angles of incidence. These are summarised in the Table below. Surface flow visualisation was carried out by means of tufts attached to various key locations on the surface.

Table EXP-A Summary Description of All Test Cases
Re Mach Incidence (deg.) Position of traverse Detailed data
L1T2 3.52x106 0.197 4.01° 35% wing element chord;

shroud t/e; 50% flap chord;

Cp on surface Cptot normal to surface
20.18° flap t/e

Table EXP-B Summary Description of All Measured Parameters and Available Data Files




L1T2 4.01° EXP_Cp_a040_slat.dat EXP_Cptot_a040_BL01.dat
EXP_Cp_a040_wing.dat EXP_Cptot_a040_BL02.dat
EXP_Cp_a040_flap.dat EXP_Cptot_a040_BL03.dat
20.18° EXP_Cp_a202_slat.dat EXP_Cptot_a202_BL01.dat
EXP_Cp_a202_wing.dat EXP_Cptot_a202_BL02.dat
EXP_Cp_a202_flap.dat EXP_Cptot_a202_BL03.dat

Table EXP-B Summary description of all measured parameters and available data files

Test Case EXP-1

Description of Experiment

The L1T2 model was mounted between turntables in the floor and the roof of the wind tunnel. Local suction around the wing/wall junctions ensured that the flow was essentially two-dimensional. Surface pressures were measured on the three components of the model using pressure tappings. Pressure measurements were made at two spanwise locations, one at approximately mid span and one near the roof. The measurements presented here are those from the mid span location. Pitot-static traverses were made at four chordwise locations to provide information on the development and interactions of the boundary layers and wakes.

Transition was set on the main element lower and upper surfaces at 12.5% retracted chord.

Boundary Data

No tunnel wall pressure data is available from the experiment. The measured free stream velocity is, however, corrected for solid blockage and the incidence is corrected to represent the effect of wall constraint. The pressure coefficients are based on free stream dynamic pressure, again corrected for solid blockage. No camber or wake blockage corrections were applied.

The wall boundary layer was removed by suction in the region of the model.

Measurement Errors

• Mach number: ±0.5%

• Angle of incidence: ±0.5%

• Pressure coefficients: ±0.1%

Measured Data

• Surface pressure coefficients on the slat, main-element and flap

• Total pressure coefficients at four chordwise locations


[1] I.R.M. Moir. Measurements on a Two-Dimensional Aerofoil with High Lift Devices, AGARD AR 303, Vol II, pp A2.1-A2.12, 1994.

© copyright ERCOFTAC 2004

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

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