Details on the Computation of Hypersonic Inlet Flows
نویسندگان
چکیده
منابع مشابه
Computation of Catalycity Eeects in Hypersonic Non-equilibrium Flows
The eeects of nite-rate wall catalyticity are evaluated by numerical simulations of hypersonic non-equilibrium ows. Several models derived from speciic gas surface chemical schemes taking into account elementary steps, such as adsorption, surface recombination and desorption, are considered. The models have been incorporated in a mixed nite-element//nite-volume code for reactive viscous ow as s...
متن کاملUnstart Coupling Mechanism Analysis of Multiple-Modules Hypersonic Inlet
The combination of multiplemodules in parallel manner is an important way to achieve the much higher thrust of scramjet engine. For the multiple-modules scramjet engine, when inlet unstarted oscillatory flow appears in a single-module engine due to high backpressure, how to interact with each module by massflow spillage, and whether inlet unstart occurs in other modules are important issues. Th...
متن کاملnew semigroup compactifications via the enveloping semigroups of associated flows
this thesis deals with the construction of some function algebras whose corresponding semigroup compactification are universal with respect to some properies of their enveloping semigroups. the special properties are of beigan a left zero, a left simple, a group, an inflation of the right zero, and an inflation of the rectangular band.
15 صفحه اولsurvey on the rule of the due & hindering relying on the sheikh ansaris ideas
قاعده مقتضی و مانع در متون فقهی کم و بیش مستند احکام قرار گرفته و مورد مناقشه فقهاء و اصولیین می باشد و مشهور معتقند مقتضی و مانع، قاعده نیست بلکه یکی از مسائل ذیل استصحاب است لذا نگارنده بر آن شد تا پیرامون این قاعده پژوهش جامعی انجام دهد. به عقیده ما مقتضی دارای حیثیت مستقلی است و هر گاه می گوییم مقتضی احراز شد یعنی با ماهیت مستقل خودش محرز گشته و قطعا اقتضاء خود را خواهد داشت مانند نکاح که ...
15 صفحه اولParametric Geometry Models for Hypersonic Aircraft: Integrated External Inlet Compression
In this paper we are investigating a method for the design and integration of 3D external compression inlet geometries on parametric geometries of air-breathing hypersonic aircraft. We view the geometries as the first stage of a mixed compression inlet. The investigations are based on waverider geometries generated with the osculating cones waverider forebody design method. The osculating cones...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: PAMM
سال: 2003
ISSN: 1617-7061,1617-7061
DOI: 10.1002/pamm.200310147