Abstract
A generic wind tunnel model for tailplane stall research was designed and experimentally investigated to establish a database for code validation. The configuration is numerically optimised to obtain large Reynolds numbers at the horizontal tailplane in a wind tunnel of limited size. It consists of a fuselage, a detachable horizontal tailplane and a tip-truncated wing, that mounts the model to the turntables of the closed test section. The wing was designed to reproduce a representative downwash in the tailplane region. The tests were conducted at a freestream Mach number of 0.16 and at a Reynolds number of 0.72 wx 106. Tailplane stall in case of natural and fixed transition was visualised by the oil-flow technique and quantified by pressure and force measurements and by the Particle Image Velocimetry of the turbulent trailing-edge separation. Numerical simulations, using the unstructured Reynoldsaveraged Navier Stokes Code TAU, are in good agreement with the experiments. They show a separation of the boundary layer starting at the trailing edge with high crossflow velocities at the outer tailplane. Depending on the boundary-layer transition, the stall occurs abruptly for natural transition, initialised by a burst of a laminar separation bubble, or gradually for fixed transition.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
T. Gerhold. Overview of the Hybrid RANS Code TAU. In: N. Kroll et al. (Ed.). ”MEGAFLOW — Numerical How Simulation for Aircraft Design”. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Vol. 89, Springer, 2005, pp. 81–92.
A. Grote and R. Radespiel. Investigation of Tailplane Stall for a Generic Transport Aircraft Configuration. In: H.-J. Rath et al. (Ed.). ”New Results in Numerical and Experimental Fluid Mechanics”. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Vol. 92, Springer, 2006, pp. 50–58.
A. Grote and R. Radespiel. ”Studies on Tailplane Stall for a Generic Transport Aircraft Configuration”. AIAA-Paper 2006-655, 44th AIAA Aerospace Sciences Meeting and Exhibit, 9–12 January 2006, Reno, Nevada, USA, 2006.
Norddeutscher Verbund für Hoch-und Höchstleistungsrechnen, www.hlrn.de
A. Krynytzky. Conventional wall corrections for closed and open test sections. In: B. Ewald (Ed.). ”Wind tunnel wall corrections”. AGARD-AG-336, RTO/NATO, 1998.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2007 Springer-Verlag Berlin Heidelberg
About this paper
Cite this paper
Grote, A., Radespiel, R. (2007). Studies on Tailplane Stall for a Generic Transport Aircraft Wind Tunnel Model. In: Tropea, C., Jakirlic, S., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics VI. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 96. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-74460-3_4
Download citation
DOI: https://doi.org/10.1007/978-3-540-74460-3_4
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-74458-0
Online ISBN: 978-3-540-74460-3
eBook Packages: EngineeringEngineering (R0)