Effect Micro Vortex Generator Hypersonic by Kumar Vivek (3 results)
- Softcover
Seller: Mispah books, Redhill, SURRE, United KingdomMispah books
Contact seller4-star sellerCondition: Used - As new
US$ 140.73
US$ 33.82 shippingShips from United Kingdom to U.S.A.Quantity: 1 available
Paperback. Condition: Like New. LIKE NEW. SHIPS FROM MULTIPLE LOCATIONS. book.
- Softcover
- Print on Demand
Seller: moluna, Greven, Germanymoluna
Contact seller5-star sellerCondition: New
US$ 49.66
US$ 56.68 shippingShips from Germany to U.S.A.Quantity: Over 20 available
Condition: New. Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. Autor/Autorin: V. Kumar VivekCompleted Masters in Aeronautical Engineering(Aerodynamics) from Hindustan Institute of Technology & Science, Chennai and undergraduate degree in Aeronautical Engineering from JRNRV Univer…sity.Currently working as Assis.
- Softcover
- Print on Demand
Seller: AHA-BUCH GmbH, Einbeck, GermanyAHA-BUCH GmbH
Contact seller5-star sellerCondition: New
US$ 59.10
US$ 70.38 shippingShips from Germany to U.S.A.Quantity: 2 available
Taschenbuch. Condition: Neu. nach der Bestellung gedruckt Neuware - Printed after ordering - The recent advances in aerospace vehicle technology demands the best possible propulsive balance to provide better thrust and minimum drag. Air-breathing engines are the best choice for the propulsion due to its minimum weight. The effic…iency of such engines depend upon the quality of air entering for combustion. This book provides complete flow analysis of both pure inline-compression and mixed-compression inlets. Two dimensional simulations were carried out with SST k- model using FLUENT. The boundary layer formed inner side of the engine had an adverse pressure gradient on the ramp producing a boundary layer separation. Due to this the boundary layer thickens and the static pressure starts to decrease whose effect leads till the trailing edge of inlet. Small wedge shaped Micro-Vortex Generator (MVG) inside the inlet smoothen the generated shock-boundary layers and thereby an efficient compression is obtained . The analysis should help shed some light on hypersonic inlet design optimization at off-design condition and should be especially useful to researchers and academicians in the field of Aerospace Engineering.
