EXPERIMENTAL RESULTS OF A MACH 10 CONICAL-FLOW DERIVED WAVERIDER TO 14-X HYPERSONIC AEROSPACE VEHICLE. doi: 10.5028/jatm.2011.03027510

Tiago Cavalcanti Rolim, Paulo Gilberto de Paula Toro, Marco Antonio Sala Minucci, Antônio Carlos de Oliveira, Roberto da Cunha Follador

Abstract


This paper presents a research in the development of the 14-X
hypersonic airspace vehicle at Institute for Advanced Studies (IEAv) from
Department of Science and Aerospace Technology (DCTA) of the Brazilian
Air Force (FAB). The 14-X project objective is to develop a higher effi cient
satellite launch alternative, using a Supersonic Combustion Ramjet
(SCRAMJET) engine and waverider aerodynamics. For this development,
the waverider technology is under investigation in Prof. Henry T.
Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN),
in IEAv/DCTA. The investigation has been conducted through ground test
campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle
characteristic was verifi ed in shock tunnel T3 where surface static pressures
and pitot pressure for Mach number 10 were measured and, using Schlieren
photographs Diagnostic Method, it was possible to identify a leading-edge
attached shock wave in 14-X lower surface.

Keywords


Hypersonics, Hypersonic systems, Shock tunnel, Schlieren, Waverider.

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