Library Subscription: Guest
Begell Digital Portal Begell Digital Library eBooks Journals References & Proceedings Research Collections
TsAGI Science Journal

ISSN Print: 1948-2590
ISSN Online: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.2015013901
pages 123-142

CHARACTERISTICS INVESTIGATION OF 2D AND 3D INTAKES OF SUPERSONIC PASSENGER AIRCRAFT

Vyacheslav Afanasievich Vinogradov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya Str., Moscow, 111116, Russian Federation
Vladimir Alekseevich Stepanov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya Str., Moscow, 111116, Russian Federation
Yakov Aleksandrovich Melnikov
Central Institute of Aviation Motors (CIAM), 2, Aviamotornaya Str., Moscow, 111116 Russia

ABSTRACT

Two intake configurations, three-dimensional (3D) and planar [two-dimensional (2D)], for a cruising (M = 1.6) supersonic passenger aircraft (SPA) are considered. The intake includes a supersonic inlet and large-curvature subsonic diffuser (SD). Preliminary incoming airflow deceleration and boundary-layer control (BLC) in the 3D inlet case are carried out with the help of a swept wedge placed in front of the inlet due to a transverse pressure gradient being formed. In the 2D inlet case, boundary-layer bleed is achieved by installing the inlet on the wedge at some height from the surface. Further deceleration is realized in a system of shocks with terminal normal one. The results of the flowing inlet with the SD and boundary-layer bleed in the throat in throttling modes at M = 0.8−1.8 were obtained with the help of numerical simulations based on the solution of the 3D Navier− Stokes equations. Flow stability was confirmed when the pressure in the SD exit section was raised 1−4 times compared with the external free-stream pressure. It was found that the total pressure recovery coefficient σ grows up to σ = 0.89−0.97 when using BLC. The drag estimations of the considered inlets−including the additive, wave drag components, and also the drag of the bleeding wedge−show that the summary drag of the 3D inlet is 1.5−3.5 times less than that of the 2D inlet in the M = 0.8−1.6 range when the efficiency of the flow deceleration in the inlet is the same.


Articles with similar content:

SPECIFIC FEATURES OF DECELERATION OF A HIGH-VELOCITY FLOW IN CONVERGENT FIXED-GEOMETRY INLETS
TsAGI Science Journal, Vol.48, 2017, issue 4
Natalya Valeryevna Guryleva, Vladimir Alekseevich Stepanov, Mikhail Anatolyevich Ivan'kin, Vyacheslav Afanasievich Vinogradov
FILM-COOLING CHARACTERISTICS OF UPSTREAM RAMP ENHANCED TURBINE BLADE SURFACE COOLING
Heat Transfer Research, Vol.48, 2017, issue 11
Paresh Halder, Jun-Hee Kim, Abdus Samad, Kwang-Yong Kim
ESTIMATION OF OPERATING CONDITIONS OF A MID-RANGE AIRCRAFT AUXILIARY POWER UNIT WITH RECEIVER INLET IN TURBULENT FLOW
TsAGI Science Journal, Vol.46, 2015, issue 4
Egor Vyacheslavovich Kazhan, Vladimir Fedorovich Tretyakov, Evgenii Petrovich Bykov
ROBUST CONTROL DESIGN TO SUPPRESS WING ROCK MOTION OF A WIND-TUNNEL AIRCRAFT MODEL IN 3DOF GIMBALS
TsAGI Science Journal, Vol.45, 2014, issue 8
Maria Evguenievna Sidoryuk
EXPERIMENTAL INVESTIGATION OF A 3D FIXED-GEOMETRY INLET FOR A SUPERSONIC BUSINESS AIRCRAFT
TsAGI Science Journal, Vol.48, 2017, issue 3
Vladimir Alekseevich Stepanov, A. Yu. Makarov, N. A. Melkonyan, Vyacheslav Afanasievich Vinogradov