In this article, a biconic re-entry model was investigated in a blow down wind tunnel at Mach 1.5, 2, 3, and 4. The main focus was on studying the longitudinal stability and aerodynamic efficiency in this flying regime. In particular, the influence of wings near the rear part of the model, their wing dihedral, and additional body flaps was investigated. While the purely biconic configuration was unstable, it could be stabilized with wings at a 20° downward pitch and with the additional body flaps. In general, a larger dihedral angle improved pitch stiffness.
Esch H. Force measurements on a model of the semi-ballistic re-entry vehicle Colibri (German). Research report IB - 39113-97A04, German Aerospace Center, 1997.
11.
Burkhart J. Conceptional systems design and mission analysis of a lift in re-entry vehicle. PhD Thesis, University of Stuttgart, Germany, 2001.
12.
Miller C, Blackstock T, Helms V, et al. An experimental investigation of control surface effectiveness and real-gas simulation for biconics. In: AIAA 21st aerospace sciences meeting, Reno, Nevada, USA, 10–13 January 1983.
13.
DaviesCBParkC. Aerodynamics of generalized bent biconics for aero-assisted, orbital-transfer vehicles. J Spacecraft Rockets1985; 22: 104–111.
14.
WartemannVWeihsHEggersT. Comparison of facetted and blunt lifting bodies for re-entry flight. In: International space planes and hypersonic systems and technologies conferences, Reston, VA: AIAA, 2017.
15.
Tarfeld F. Experimental study on a liquid fly-back booster configuration in wind tunnels. In: 12th AIAA international space planes and hypersonic systems and technologies, Norfolk, VA, USA, 15–19 December 2003, p. 7056.
16.
Sippel M, Klevanski J, Burkhardt H, et al. Progress in the design of a reusable launch vehicle stage. AIAA-2002-5220, 2002.
17.
Eggers T. Longitudinal stability and trim of an Ariane 5 fly-back booster. In: 12th AIAA international space planes and hypersonic systems and technologies, Norfolk, VA, USA, 15–19 December 2003, p. 7055.
18.
Eggers T. Aerodynamic behaviour of a liquid fly-back booster in transonic cruise flight. In: 21st AIAA applied aerodynamics conference, Orlando, FL, USA, 23–26 June 2003, p. 3422.
19.
Esch H. The 0.6 x 0.6m tri-sonic wind tunnel (TMK) of the DFVLR in Köln-Porz (German). Internal Report 86-21, Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt, 1986.
20.
TropeaCYarinALFossJF. Handbook of experimental fluid mechanics, Berlin, Heidelberg: Springer, 2007.
