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Jet in supersonic crossflow
Based on research into jets in supersonic crossflow carried out by the authors' team over the past 15 years, this book summarizes and presents many cutting-edge findings and analyses on this subject. It tackles the complicated mixing process of gas jets and atomization process of liquid jets in supersonic crossflow, and studies their physical mechanisms. Advanced experimental and numerical techniques are applied to further readers' understanding of atomization, mixing, and combustion of fuel jets in supersonic crossflow, which can promote superior fuel injection design in scramjet engines. The book offers a valuable reference guide for all researchers and engineers working on the design of scramjet engines, and will also benefit graduate students majoring in aeronautical and aerospace engineering.
Book
Effect of Height on the Supersonic Flow over a Blunt Vertical Fin
Understanding how protrusions, such as fins attached to flat or streamlined bodies, affect aerodynamics, especially in high-speed contexts, is vital for aerospace applications. These protrusions significantly influence overall aerodynamics and require a comprehensive understanding for accurate analysis and prediction of aerodynamic performance. This understanding is particularly critical in supersonic flight, where even minor aerodynamic disturbances can impact vehicle stability and efficiency. Therefore, a thorough understanding of protrusion-induced flow phenomena is essential for advancing aerospace engineering and improving supersonic vehicle performance and safety. The present paper focuses on the complex supersonic flow over a vertical fin, using a combination of experimental and computational methods. The study aims to understand how variations in fin height influence the behavior of the Lambda shock and any resulting changes in shock length. Specifically, the paper investigates different fin height-to-diameter (H/D) ratios ranging from 0.5 to 1.5 in steps of 0.25. To achieve this, both experimental testing in a supersonic wind tunnel and numerical simulations using the commercial CFD tool ANSYS-FLUENT are employed. Through this dual approach, the paper seeks insights into the characteristics of the Lambda shock and its effects on key aerodynamic parameters, such as shock strength and drag coefficient. By thoroughly investigating these aspects, the paper contributes to a deeper understanding of the complex flow phenomena associated with supersonic flow over vertical fins, potentially guiding the design and optimization of aerospace vehicles. The outcomes indicate that a fin height of 12 mm (H/D=1.0) provides the best balance in terms of pressure distribution, Lambda shock length, and drag coefficient, making it the optimal choice for enhancing aerodynamic stability and performance in supersonic conditions.
Journal Article
Chasing the demon : a secret history of the quest for the sound barrier, and the band of American aces who conquered it
\"The New York Times bestselling author of Viper Pilot chronicles another thrilling chapter in American aviation history: the race to break the sound barrier. In the aftermath of World War II, the United States accelerated the development of technologies that would give it an advantage over the Soviet Union. Airpower, combined with nuclear weapons, offered a formidable check on Soviet aggression. In 1947, the United States Air Force was established. Meanwhile, scientists and engineers were pioneering a revolutionary new type of aircraft which could do what no other machine had ever done: reach mach 1--a speed faster than the movement of sound--which pilots called \"the demon.\" Chasing the Demon recreates an era of excitement and danger, adventure and innovation, when the future of the free world was at stake and American ingenuity took the world from the postwar years to the space age. While the pressure to succeed was high, it was unknown whether man or machine could survive such tremendous speeds. A decorated military pilot with years of experience flying supersonic fighter jets, Dan Hampton reveals in-depth the numerous potential hazards that emerged with the Air Force's test flights: controls broke down, engines flamed out, wings snapped, and planes and pilots disintegrated as they crashed into the desert floor. He also introduces the men who pushed the envelope taking the cockpits of these jets, including World War II ace Major Dick Bong and twenty-four-year-old Captain Chuck Yeager, who made history flying the Bell X-1 plane faster than the speed of sound on October 14, 1947. Illustrated with thirty black-and-white photographs, Chasing the Demon recalls this period of the emerging Cold War and the brave adventurers pursing the final frontier in aviation\"-- Provided by publisher.
Book
Essentials of supersonic commercial aircraft conceptual design
Provides comprehensive coverage of how supersonic commercial aircraft are designed
This must-have guide to conceptual supersonic aircraft design provides a state-of-the art overview of the subject, along with expert analysis and discussion. It examines the challenges of high-speed flight, covers aerodynamic phenomena in supersonic flow and aerodynamic drag in cruising flight, and discusses the advantages and disadvantages of oblique wing aircraft.
Essentials of Supersonic Commercial Aircraft Conceptual Design is intended for members of a team producing an initial design concept of an airliner with the capability of making supersonic cruising flights. It begins with a synopsis of the history of supersonic transport aircraft development and continues with a chapter on the challenges of high-speed flight, which discusses everything from top level requirements and cruise speed requirements to fuel efficiency and cruise altitude. It then covers weight sensitivity; aerodynamic phenomena in supersonic flow; thin wings in two-dimensional flow; flat wings in inviscid supersonic flow; aerodynamic drag in cruising flight, and aerodynamic efficiency of SCV configurations. The book finishes with a chapter that examines oblique wing aircraft.
* Provides supersonic aircraft designers with everything they need to know about developing current and future high speed commercial jet planes
* Examines the many challenges of high-speed flight
* Covers aerodynamic phenomena in supersonic flow and aerodynamic drag in cruising flight
* Discusses the advantages and disadvantages of oblique wing aircraft
Essentials of Supersonic Commercial Aircraft Conceptual Design is an ideal book for researchers and practitioners in the aerospace industry, as well as for graduate students in aerospace engineering.
eBook
Systematic Assessment of DGFEM Accuracy for Supersonic Flow
The modern High-Order Discontinuous Galerkin Finite Element Method (DGFEM) is considered. The method offers the advantages of the finite volume and the traditional finite element methods within a unified framework. However, the performance of the DGFEM may be affected for supersonic flow because of the limiters. Hence, a systematic assessment of the accuracy of the DGFEM is performed. The improved accuracy of the DGFEM is quantified and the benefits are highlighted.
Journal Article
Feasibility study of hydrogen-ammonia synergistic combustion in scramjets across broad Mach ranges
Ammonia shows advantages over hydrocarbon fuels for high-Mach scramjet engines, including superior cooling capacity and carbon-free combustion. However, its operation at lower Mach numbers remains challenging. Here, we successfully demonstrate ammonia-hydrogen ignition at Mach 3 and sustained combustion at Mach 6, confirming the feasibility of hydrogen-ammonia synergistic supersonic combustion. Compared to hydrogen combustion, ammonia addition at low Mach numbers does not alter flame paths but increases flame establishment times by 57.1% upstream and 100% downstream. Both global flame establishment and cavity ignition times are longer under the upstream scheme. At high Mach numbers, two distinct combustion modes are observed. Upstream hydrogen injection ignites more ammonia and produces more intense combustion than downstream injection. These results demonstrate the feasibility of ammonia-fueled scramjets operating across a broad Mach range.
Ammonia offers benefits like easy storage, high cooling capacity, and carbon-free combustion for high-Mach scramjets, but its low-Mach operation is challenging. Here, authors demonstrate the feasibility of ammonia-hydrogen ignition at Mach 3 and sustained combustion at Mach 6.
Journal Article
Experimental investigation of mini supersonic wind tunnel for flow visualization
The present study proposes to design, fabricate and investigate a miniature supersonic wind tunnel at an affordable cost, safe to operate, and reliable for education purposes. The configuration consists of a high pressure reservoir, and mini tunnel which will be used for providing the supersonic flow over aerodynamic models. To design the mini supersonic wind tunnel, the method of characteristics is used to ensure that any shocks that arise in contact with the surface do not impact the uniformity and velocity of the flow through the duct. To achieve the supersonic flow, the nozzle contour of the supersonic portion of the wind tunnel is built in such a way that the shocks nullify each other and have zero effect on the velocity of the flow. For compressible flow visualization, an affordable Schlieren setup consisting of a torch, mirrors, and a mobile camera is used for flow visualization. Finally, the visualization results of the present study is in good relation with the theoretical calculations. The present facility is also calibrated by measuring the oblique shock angle in the test section, in the range of Mach number 1.6 to 1.8.
Journal Article
Identification of efficient geometries for variable pitot inlets for supersonic transport
Purpose
This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation.
Design/methodology/approach
The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced.
Findings
The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6.
Originality/value
Hence, the technology of circular variable pitot inlets for supersonic transport aircraft could be a way to achieve the ambitious ecological, safety and economic goals for future civil aviation.
Journal Article
Study on solid powder fuel transport characteristics and mixing degree in scramjet combustor
The powder scramjet engine is considered the best engine for hypersonic weapons because of its advantages of easy adjustment, flame stability, and high efficiency. However, due to the extremely short residence time of particle fuel in the combustion chamber under high Mach conditions, there is a risk of fuel mixing. Based on the existing combustion chamber models of scramjet engines, this paper proposes a new solid fuel blending enhancement structure by combining shock generator structure and transverse jet and compares the performance and mass transfer characteristics of different shock generators. The CFD method is used to solve the RANS formula to simulate the particle transfer process, and the SST k-ω model is used to calculate the complex turbulence. It was found that when the reverse shock generator was used, the mixing degree of solid particles was higher.
Journal Article
Stability of supersonic boundary layer over an unswept wing with a parabolic airfoil
Under the low-noise Mach 3 flight conditions for a supersonic passenger aircraft having unswept wings with a thin parabolic airfoil, laminar-turbulent transition is due to amplification of the first mode. Stability of a local self-similar boundary layer over such a wing is investigated both using the eN method in the framework of linear stability theory and direct numerical simulation (DNS). It is found that the instability amplitude should reach a maximum over the entire spectral range above the profiles of 2.5% and thicker. The locus of maximum appears at the trailing edge and moves to the leading edge as the profile becomes thicker, while the maximum amplitude decreases. The theoretical findings are supported by DNS of the linear wave packets propagating in the boundary layer. Significance of these results to the design of laminar supersonic wings is discussed.
Journal Article