Summary
The design, construction, manufacturing and geometric properties of a generic 65° Delta Wing for the International Vortex Flow Experiment 2 are described. Briefly, the measurement equipment implemented in the model and the external sensors are specified. A wind tunnel investigation has been performed and the results for two different leading edge geometries (sharp and rounded) at three angles of attack are discussed in detail. Further, the results are compared with the ones obtained by NASA and also with computational results. Partly developed (α = 13°) and fully developed (α = 18°) leading edge vortices as well as vortex breakdown (α = 23°) are considered.
This is a preview of subscription content, log in via an institution to check access.
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
C. Breitsamter: “Turbulente Strömungsstmkturen an Flugzeugkonfigurationen mit Vorderkantenwirbeln”. Dissertation, Technische Universität München, Hexbert Utz Verlag, ISBN 3-89675-201-4, 1997.
J. Chu, J. M. Luckring: “Experimental Surface Pressure Data Obtained on 65° Delta Wing Across Reynolds Nummlmr and Mach Nummber Ranges”. NASA-TM-4645, Volume 1-Sharp Leading Edge, 1996.
F. Ghafarri: RTO-MP-AVT-113, Personal communication, 2004.
D. Hummel, G. Redoker: “A now vortex flow exporimcat for computer code validation”. Paper 8, RTO Symposium on Advanced Flow Management, Part A-Vortex flow and high angle of attack, Leno, Norway, 7-11 May 2001.
D. Hummel: “Effects of boundary layer formation on the vortical flow above slender delta wing”. Paper 30, RTO Symposium on Enhancement of NAIO Military Flight Vehicle Performance by Management of Intexacting Boundary Layex Transition and Separation, Prague, Czech Republic, 4-7 Oct. 2004.
J. M. Luckring: “Reynolds Number, Compressibility, and Leading-Edge Bluntness Effects on Delta-Wing Aerodynamics”. ICAS-2004-4.1.4, 24th Congress of the International Council of the Aeronautical Sciences, Yokohama, Japan, 29 Aug.-3. Sept. 2004.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2006 Springer-Verlag Berlin Heidelberg
About this paper
Cite this paper
Furman, A., Breitsamter, C. (2006). Delta Wing Steady Pressure Investigations for Sharp and Rounded Leading Edges. In: Rath, HJ., Holze, C., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics V. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 92. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-33287-9_10
Download citation
DOI: https://doi.org/10.1007/978-3-540-33287-9_10
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-33286-2
Online ISBN: 978-3-540-33287-9
eBook Packages: EngineeringEngineering (R0)