High performance supersonic missile inlet design using automated optimization

Zha, Gecheng; Smith, Donald; Schwabachei, Mark; Rasheed, Khaled; Gelsey, Andrew; Knight, Doyle; Haas, Martín

doi:10.2514/6.1996-4142

Cited by 25 publications

(16 citation statements)

References 11 publications

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“…In addition to overall aircraft shaping, a redesign of the inlet is required in order to achieve low-boom flight. The inlet must satisfy basic design principles used to decelerate the flow to subsonic speeds before entering the engine while also satisfying additional requirements for a quiet supersonic aircraft (4)(5)(6)(7)(8)(9)(10)(11)(12)(13) . The inlet design considered herein is based on a concept proposed by Conners and Howe (6) .…”

Section: Previous Studiesmentioning

confidence: 99%

Simulations of a low-boom, axisymmetric, external compression inlet

Coyne

Loth

Koncsek

et al. 2013

Aeronaut. j. (1968)

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Computational simulations have been used to study a new low-boom, axisymmetric, external compression supersonic inlet with an on-design Mach number of 1·7. The inlet incorporates a relaxed compression surface with a near-zero cowl angle to help reduce external oblique shock waves due to spillage and cowl geometry. To reduce mechanical complexity the inlet is designed with zero-bleed. To understand the impact on performance and shock overpressure caused by the inlet itself, several throat and diffuser designs were simulated. The computations utilised a Reynolds-averaged Navier-Stokes code. Inflow properties were held consistent with the operational characteristics of the NASA GRC 8' × 6' Supersonic Wind Tunnel (SWT) for experimental testing of the inlet of Mach 1·67 at a Reynolds number of 5·4 × 10 6 . Stagnation pressure recovery performance for the baseline condition exceeded 94% at design mass flow rates, and reduced only slightly with increases in Mach number (consistent with theoretical predictions) and extension of cowl position. The simulations also showed that the relaxed compression surface combined with the near-zero cowl angle helps to significantly reduce external oblique shocks This is partly due to the reduced inlet spillage in combination with a reduced overall turning angle placed on the free-stream flow relative to the cowl shape.

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Section: Previous Studiesmentioning

confidence: 99%

Simulations of a low-boom, axisymmetric, external compression inlet

Coyne

Loth

Koncsek

et al. 2013

Aeronaut. j. (1968)

View full text Add to dashboard Cite

show abstract

“…The cost of analyzing the keel with PMARC is orders of magnitude greater than the cost of evaluating the algebraic formula, so it would be potentially very bene cial to perform most of the optimization at the rst level. In the supersonic missile inlet design domain Zha et al 1996 , w e h a ve used an empirical code known as NIDA to analyze a missile inlet rapidly, and a computational uid dynamics code known as GASP to analyze it with greater accuracy. Analyzing a single missile inlet with GASP takes about one CPU week, which makes it infeasible to perform optimizations with GASP using our current computational resources.…”

Section: Discussionmentioning

confidence: 99%

Multi-level simulation and numerical optimization of complex engineering designs

Schwabacher

Gelsey

1996

6th Symposium on Multidisciplinary Analysis and Optimization

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Multi-level representations have been studied extensively by arti cial intelligence researchers. We utilize the multi-level paradigm to attack the problem of performing multidiscipline engineering design optimization in the presence of many local optima. We use a m ultidisciplinary simulator at multiple levels of abstraction, paired with a multi-level search space. We tested the resulting system in the domain of conceptual design of supersonic transport aircraft, and found that using multilevel simulation and optimization can decrease the cost of design space search b y one or more orders of magnitude.

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“…As we have seen earlier, this was evident already in the early 1950s [4] and it became an increasing concern as the majority of designs started featuring intakes that inevitably captured a streamtube that had been in contact with the fuselage (i.e., they were not of the nose-or wingmounted pitot variety). We have discussed the drag vs pressure So-called multilevel design techniques have been found by some to be an effective compromise [21]. These involve running the bulk of the optimization study on a low cost, low-fidelity physics-based prediction, occasionally validated/calibrated by a high-fidelity (typically Reynoldsaveraged Navier-Stokes) solver.…”

Section: B Forebody Boundary Layermentioning

confidence: 99%

Tradeoffs in Jet Inlet Design: A Historical Perspective

Sóbester

2007

Journal of Aircraft

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The design of the inlet(s) is one of the most demanding tasks of the development process of any gas turbine-powered aircraft. This is mainly due to the multi-objective and multidisciplinary nature of the exercise. The solution is generally a compromise between a number of conflicting goals and these conflicts are the subject of the present paper. We look into how these design tradeoffs have been reflected in the actual inlet designs over the years and how the emphasis has shifted from one driver to another. We also review some of the relevant developments of the jet age in aerodynamics and design and manufacturing technology and we examine how they have influenced and informed inlet design decisions.

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High performance supersonic missile inlet design using automated optimization

Cited by 25 publications

References 11 publications

Simulations of a low-boom, axisymmetric, external compression inlet

Simulations of a low-boom, axisymmetric, external compression inlet

Multi-level simulation and numerical optimization of complex engineering designs

Tradeoffs in Jet Inlet Design: A Historical Perspective

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