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I. N. Larina

Bio: I. N. Larina is an academic researcher. The author has contributed to research in topics: Reynolds number & Choked flow. The author has an hindex of 1, co-authored 1 publications receiving 1 citations.

Papers
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Journal ArticleDOI
TL;DR: In this article, a numerical simulation of supersonic flow past a sphere with a jet exhausting from the front point of the sphere into the flow at large is presented, where the effect of shielding from the oncoming stream is revealed.
Abstract: The experimental investigation of supersonic flow past a sphere with a jet exhausting from the front point of the sphere into the flow at large [1] and moderate [2] Reynolds numbers Re has revealed an effect of shielding from the oncoming stream, this leading to a decrease in the drag coefficient of the sphere and of the energy flux to it. A numerical simulation of the flow has been made in the case of supersonic flow past a sphere with a sonic jet from a nozzle situated on the symmetry axis in the continuum regime [3]. In the present paper, this problem is investigated for flow of a rarefied gas on the basis of numerical solution of a model kinetic equation for a monatomic gas.

3 citations


Cited by
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Journal ArticleDOI
TL;DR: A comprehensive survey on the field of forebody shock control devices is presented in this article, where the authors categorize the various forebody shocks control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge.

46 citations

Journal ArticleDOI
TL;DR: In this article , a review of shock reduction techniques, including passive, active, and hybrid flow control, is presented, along with the implications in the usage of these technologies along with potential gaps.
Abstract: Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

4 citations

Book ChapterDOI
01 Jan 2023
TL;DR: In this paper , a comprehensive literature survey is presented to disclose the flow structure of the coolant jet in different jet and domain conditions, and effective factors associated with flow structure and cooling mechanism are introduced and compared to show the foremost parameters in this approach.
Abstract: Injection of the cooling gas from the tip of the nose cone, known as opposing jet, is the most conventional technique for the reduction of heat and drag on the forebody of high-speed vehicles. In this chapter, the mechanism of cooling and drag reduction by the opposing jet is fully discussed. Comprehensive literature survey is presented to disclose the flow structure of the coolant jet in different jet and domain conditions. Effective factors associated with the flow structure and cooling mechanism are introduced and compared to show the foremost parameters in this approach. Efficient injection configuration is also defined in this chapter according to the operating condition of the high-speed vehicles.

1 citations