In the F16 Sliding project is a wind tunnel model of a 2D airfoil. This designed for aero-acoustic measurements trainer should be seen as an adaptation of the existing F16 model.
The scope of the SHT comprises the construction, design and Production of newly designed components.
Technical details of the model:
Flow Rate: 60 m/s
Abbildung 1: Von Mises comparative stress of Slathalters
Research Project Background
High lift devices such as those installed in scale F16 Sliding, serve to make a compromise between a high lift for takeoff and landing and low flow resistance in the cruise.
The standard in commercial aircraft flaps and slats create a gap to the main wing, by the tendency for flow separation is significantly reduced in the extended state. However, due to the flow through this gap an undesirable rise in the acoustic load on landing operations. this should diverse Vorflügel- and flap configurations will be tested and evaluated for their aeroacoustic properties in experimental studies.
After initial studies with a 2D profile on AWB (Acoustic Wind Tunnel Braunschweig) and NCA (Low Speed Wind Tunnel Braunschweig) were carried out, is now in ONERA F2 wind tunnel followed by a measurement campaign for donating installation.
For the wind tunnel tests is modern Strömungsmesstechnik as Particel image Velocitry (PIV), but also acoustic measurement technology used. In addition, in half length profile, the pressure distribution is determined via pressure taps on Slat, Wing and Flap.
Challenges in the design and manufacture
Originally designed for the AWB F16 model with a span of 800 mm be extended for measurements in the F2 channel on both sides according to the channel width of 1600 mm.
Additional support to the main wing tips allow the model recording under the gefordertern sliding angle of 30 °.
One challenge the requirement may represent compliance with the maximum permissible deformation of the wing, which is particularly affected by the donating installation on the main wing holder. This main wing holders should be dimensioned such that maintaining the deformation small, the contour very aerodynamic shape andin an optical access for PIV measurements is ensured.
To determine the maximum deformation an FEM model of the F16 model with ANSYS Workbench was created and optimized the contour of the main wing holder accordingly. From strength point of view, the newly constructed, aligned in the flow direction Slathalter were the focus. Since the position of the holder pockets on Slat and main wing was given, there was only limited scope for the dimensioning of the holder. At the same time due to the shifting mounting a complex stress state.