Experimental Testing of a Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition

Smart, Michael K.

doi:10.2514/2.5774

Cited by 104 publications

(46 citation statements)

References 5 publications

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“…As shown in Figure 1, the REST [13] can only realize the geometric shape transition but not the real aerodynamic transition. In the wind tunnel test of REST, the experimental result supported this point as the inlet tested could not capture all the upstream [14] . Hence, the object of this paper is to make a new inward turning inlet, which is named as section controllable internal waverider (SCIW) inlet.…”

supporting

confidence: 66%

Design concept of three-dimensional section controllable internal waverider hypersonic inlet

You

De-wang

2009

Sci. China Ser. E-Technol. Sci.

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A new hypersonic inlet named three-dimensional section controllable internal waverider inlet is presented in this paper to achieve the goal of section shape geometric transition and complete capture of the upstream mass. On the basis of the association between hypersonic waverider airframe and streamtraced hypersonic inlet, the waverider concept is extended to yield results for the internal flows, namely internal waverider concept. It is proven theoretically that not osculating cones but osculating axisymmetric theory is appropriate for the design of section controllable internal waverider inlet. And two design methods out of the internal waverider concept are proposed subsequently to construct two inlets with specific section shape request, triangle to ellipse and rectangle to ellipse ones. The calculation results show that the inlets are capable of keeping their shock structures and the main flow characteristics exactly as their derived flowfield. Further, the inlets successfully capture all the upstream mass despite their complicated cross-section transitions. It is believed that the concept proposed explores a new way of designing three-dimensional hypersonic inlets with special demand of section shape transition. However, the detailed flow characteristic and the performance of the internal waverider inlets are still under investigation. section controllable, internal waverider, hypersonic inlet, osculating flow, all mass captureThe new design concept of inward turning hypersonic inlet [1] has received considerable attention in the research community of hypersonic inlet design. It has been proven lately that the inlet holds the potential of better aerodynamic performance than those with conventional compression styles. For example, the JAWS [2,3] developed by U.S. Air Force Research Laboratory (AFRL) got a 24.87% net thrust addition compared with a typical two-dimensional planar hypersonic inlet. In June 2007, the hypersonic collaborative Australia/United States experiment (HyCAUSE) [4,5] flight experimental scramjet engine validated the performance of another three-dimensional inward turning hypersonic inlet. Recently, Lockheed has announced that their next generation hypersonic aircraft, Force Application and Launch from CONUS (FALCON) [6,7] , will also contain two modules of the innovative three-dimensional inward turning inlet. In the critical reviews [8][9][10] , Billig from Johns Hopkins University, stated the foundation of the concept, detailed design method as well as the performance of streamtraced inlet, an important member of the inward turning inlets. More significantly, it is believed [10] that the threedimensional inward turning inlet will lead the hypersonic inlet research in the future and consequently bring about a revolution in scramjet propulsion technology.The ongoing three-dimensional hypersonic inlets include Busemann, JAWS, modular waverider, rectangular to elliptical shape transition (REST) and rectangular to circular shape transition (RCST) ones. According to their integration manner...

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supporting

confidence: 66%

Design concept of three-dimensional section controllable internal waverider hypersonic inlet

You

De-wang

2009

Sci. China Ser. E-Technol. Sci.

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“…As trading-off, inward turning inlet configured hypersonic vehicles are brought forwards into practical phase. M. Smart et al [7][8][9][10][11] carried out a series of researches on designing the truncated Busemann inlet with section variation for the purpose of less difficult integration. A Taylor-MacColl equation governed flow field was solved to parameterize the inlet wall profiles.…”

Section: Introductionmentioning

confidence: 99%

“…Isolator and combustor length influence the whole scale of exterior wingbody design phase. M. Smart [7,8] demonstrated an isolator-combustor integrated modeling procedures and predicted the isolator variation and thermal choke behaviors. S. Torrez et al [13], C. Birzer et al [14], N. Gupta [15] and K. Tran [16] structured various scramjet models with different purposes: accelerated (not real-time) detailed scramjet performance observation, simulation based simplified scramjet model, scalable modular scramjet models and user accessible open source scramjet analysis code respectively.…”

Section: Introductionmentioning

confidence: 99%

An aircraft-propulsion geometry/performance collaborative design method

Tian

Gong

2012

IEEE 10th International Conference on Industrial Informatics

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High performance and economic gains are treated as the main target for future aerospace product design. An inward turning inlet equipped hypersonic vehicle parameterization procedure was devised for collaboration of wingbody and scramjet propulsion system modeling. Top design parameters (free-stream Mach number, flight altitude, mission requests, etc.) drive the overall collaborative system construction and both the scramjet engine geometry and wingbody profiles are conveniently generated using the NURBS toolbox and streamline tracing method within the programs developed in this paper. An accelerated digital real time hypersonic vehicle-propulsion integrated controlled plant was prepared for advanced controlling algorithm tests and further researches.

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“…The final REST inlet geometry created for the current study had an overall geometric contraction ratio of 5.80 and an internal contraction ratio of 2.08. Experimental testing of a previous REST inlet with an internal contraction ratio of 2.15 at Mach 6.12 [22] showed that it was self-starting. Based on this information, the current REST inlet was also expected to be self-starting.…”

Section: A Rest Inlet With Inlet Injectionmentioning

confidence: 99%

Application of Inlet Injection to a Three-Dimensional Scramjet at Mach 8

Turner

Smart

2010

AIAA Journal

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An investigation of inlet injection in a scramjet having a three-dimensional inlet and an elliptical combustion was undertaken. Experiments were conducted using a test flow simulating a Mach 8.1 flight condition with an altitude of 32 km. The objective was to determine the feasibility of reducing the combustion-chamber length by injection of hydrogen fuel in the inlet. The study involved a self-starting three-dimensional inlet with an overall geometric contraction ratio of 5.80, of which 2.08 was internal. The fuel was injected through multiple portholes in the forward portion of the inlet to allow significant mixing upstream of the combustion chamber. The divergent elliptical combustion chamber had a length sized for fuel ignition and combustion only and used a fluid-dynamic ignition scheme requiring no physical obstructions to the flowpath. Results indicated that inlet injection produced robust combustion at good combustion efficiency over a large fueling range up to an equivalence ratio of 0.92. A further key result was that no evidence of combustion was observed in the inlet. These experiments suggest that fuel injection in the inlet is a promising concept for higher-speed scramjet applications.

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Experimental Testing of a Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition

Cited by 104 publications

References 5 publications

Design concept of three-dimensional section controllable internal waverider hypersonic inlet

Design concept of three-dimensional section controllable internal waverider hypersonic inlet

An aircraft-propulsion geometry/performance collaborative design method

Application of Inlet Injection to a Three-Dimensional Scramjet at Mach 8

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