Performance of Various Truncation Strategies Employed on Hypersonic Busemann Inlets

Ramasubramanian, Vijay; Lewis, Mark J.; Starkey, Ryan P.

doi:10.2514/6.2009-7249

Cited by 6 publications

(2 citation statements)

References 7 publications

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“…However, the impossibility of conical flow downstream of the singular ray prevents this matching from being exact and leads to non-uniformity downstream in the conical compression. Ramasubramanian et al 7 explored matching various velocity components on the singular ray for a hypersonic application, and showed that the ICFA leading edge can be used to improve performance over simple truncation. However, effects on flow uniformity and distortion, important in the present context, were not considered.…”

Section: B Internal Conical Flow "A"mentioning

confidence: 99%

“…Also, the lack of an initial inward deflection places all required structural thickness to be outside the nacelle, and defeats the purpose of using an inward-turning flowfield to reduce sonic boom and drag. Techniques for truncation of Busemann flowfields for hypersonic applications have been reported [3][4][5][6][7][8] but all introduce significant nonuniformity in the outflow.…”

Section: Introductionmentioning

confidence: 99%

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Inward-Turning Streamline-Traced Inlet Design Method for Low-Boom, Low-Drag Applications

Otto

Trefny

Slater

2016

Journal of Propulsion and Power

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A new design method for inward-turning, streamline-traced inlets is presented. Resulting designs are intended for low supersonic, low-drag, low-boom applications such as that required for NASA's proposed low-boom flight demonstration aircraft. A critical feature of these designs is the internal cowl lip angle that allows for little or no flow turning on the outer nacelle. Present methods using conical-flow "Busemann" parent flowfields have simply truncated, or otherwise modified the stream-traced contours to include this internal cowl angle. Such modifications disrupt the parent flowfield, reducing inlet performance and flow uniformity. The method presented herein merges a conical flowfield that includes a leading shock with a truncated Busemann flowfield in a manner that minimizes unwanted interactions. A leading internal cowl angle is now inherent in the parent flowfield, and inlet contours traced from this flowfield retain its high performance and good flow uniformity. CFD analysis of a candidate inlet design is presented that verifies the design technique, and reveals a "starting" issue with the basic geometry. A minor modification to the cowl lip region is shown to eliminate this phenomenon, thereby allowing starting and smooth transition to sub-critical operation as back-pressure is increased. An inlet critical-point total pressure recovery of 96% is achieved based on CFD results for a Mach 1.7 freestream design. Correction for boundary-layer displacement thickness, and sizing for a given engine airflow requirement are also discussed.

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Section: B Internal Conical Flow "A"mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Inward-Turning Streamline-Traced Inlet Design Method for Low-Boom, Low-Drag Applications

Otto

Trefny

Slater

2016

Journal of Propulsion and Power

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Design of an Internal Osculating Waverider Intake

Noftz¹,

Shuck²,

Jewell³

et al. 2023

Journal of Propulsion and Power

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The design of an inward-turning high-speed three-dimensional streamline-traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and internal conical flow-A solution are used as the basic isentropic compressive streamline. This new contour provides efficient compression, high flow uniformity, and straight leading-edge shocks of equal strength. Additionally, a novel method for constructing the inlet cowl is presented. The combined process leads to a new method of high-speed intake design. A generic shape-transitioned intake is constructed and named the Indiana inlet for the Indiana universities that contributed to the project. Computational fluid dynamic results are assessed to validate the design method for the two-dimensional parent flowfields and the full three-dimensional design.

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Streamline Tracing Technique Based Design of Elliptical-to-Rectangular Transitioning Hypersonic Inlet

Rosli

Takahashi

Satou

et al. 2013

31st AIAA Applied Aerodynamics Conference

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Performance of Various Truncation Strategies Employed on Hypersonic Busemann Inlets

Cited by 6 publications

References 7 publications

Inward-Turning Streamline-Traced Inlet Design Method for Low-Boom, Low-Drag Applications

Inward-Turning Streamline-Traced Inlet Design Method for Low-Boom, Low-Drag Applications

Design of an Internal Osculating Waverider Intake

Streamline Tracing Technique Based Design of Elliptical-to-Rectangular Transitioning Hypersonic Inlet

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