Design and development of an air intake for a supersonic transport aircraft.

Rettie, I. H.; Lewis, W. G. E.

doi:10.2514/3.43977

Cited by 11 publications

(6 citation statements)

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“…The spinner is modeled with an elliptic profile with an aspect ratio of length-to-diameter of 2.0. The cross-sectional area of the engine face (A2) is based on the annular area formed by the circular engine face and spinner hub diameter and is A2 = 9.3918 ft 2 . Figure 1 shows the shapes of the engine face and spinner.…”

Section: Engine Facementioning

confidence: 99%

“…If the cowl lip interior angle is less than the flow angle, θclip < θcb1, and the static pressure downstream of the shock is not beyond a critical value, then a strong oblique shock can be established. The Concorde inlet [2] was able to establish a strong oblique shock, and so, reduce the loss of total pressure across the terminal shock.…”

Section: E Throat Sectionmentioning

confidence: 99%

“…As Table 3 shows, this choice yields the highest total pressure ratio through the external supersonic diffuser. This choice was also guided by the knowledge that the Concorde [2] inlet also used this configuration with the intent that the isentropic compression smoothed the interaction with the boundary layer better than an oblique shock. This choice also anticipated a variable-geometry ramp for the third stage of the external supersonic diffuser that would rotate about a point near the isentropic second stage.…”

Section: A Mach 17 Inlets: External Supersonic Diffusermentioning

confidence: 99%

“…An inlet for M0 = 2.0 involved greater supersonic compression than the inlets for M0 = 1.4 and 1.7. The inlet for the Concorde [2] aircraft provided some guidance for some of the design factors. An external supersonic diffuser with three stages (Nstg = 3) was selected with the second stage being an isentropic stage, which was used for the Concorde inlet, as well as, the inlets for M0 = 1.7.…”

Section: G Mach 20 Inletmentioning

confidence: 99%

“…Current commercial supersonic aircraft are being designed for flight between Mach 1.4 to just greater than Mach 2.0 [1]. The inlet for the Concorde aircraft [2] provides a useful reference for inlet design for this range of Mach numbers. The Concorde cruised at Mach 2.0 and used a two-dimensional, external-compression inlet to provide a stable terminal shock system.…”

Section: Iintroductionmentioning

confidence: 99%

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Design Factors for Two-Dimensional, External-Compression Supersonic Inlets

Slater

2020

AIAA Scitech 2020 Forum

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Geometric and aerodynamic design factors were studied for the design of two-dimensional, external-compression inlets operating at a freestream Mach number of Mach 1.7. Computational simulations of the inlet flows were performed to obtain the inlet performance metrics consisting of the inlet flow rates, total pressure recovery, and total pressure distortion at the engine face. The key design factors identified included the external diffuser Mach number, cowl lip interior angle, bleed slot length, throat section aft centerbody slope, and subsonic diffuser length. Using the results of the Mach 1.7 inlet study, inlets were designed for Mach 1.4 and 2.0. The results provide useful insight on the significance of the design factors for the design of such inlets for commercial supersonic aircraft.

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Section: Engine Facementioning

confidence: 99%

Section: E Throat Sectionmentioning

confidence: 99%

Section: A Mach 17 Inlets: External Supersonic Diffusermentioning

confidence: 99%

Section: G Mach 20 Inletmentioning

confidence: 99%

Section: Iintroductionmentioning

confidence: 99%

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Design Factors for Two-Dimensional, External-Compression Supersonic Inlets

Slater

2020

AIAA Scitech 2020 Forum

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Propulsion Integration: Supersonic Transport Aircraft

Sóbester

2010

Encyclopedia of Aerospace Engineering

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The integration of the propulsion system is one of the most important aspects of the design of a supersonic aircraft, as it has a strong influence on performance, safety, and reliability. Here we examine some of the propulsion integration issues specific to transport aircraft cruising at Mach numbers between 1 and 2.5, a performance bracket that includes Concorde, the only commercial passenger transport ever to have entered regular airline service. Most of the chapter is centered on the fundamental design decisions related to the design of the general layout of the propulsion system and to the conceptual design of the air intake system. The latter merits particular attention as the wide range of freestream velocities encountered by the intakes during a typical mission demand a robust, usually variable geometry, closely integrated with the design of the rest of the airframe. We devote a section to a more detailed analysis of Concorde's propulsion system and we also touch on some of the computational engineering aspects of modern propulsion integration design.

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Free-Jet Testing of a Supersonic Engine/Intake Combination

Morriss¹,

Williams

1970

Aeronaut. j.

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The design and development of aircraft powerplants for sustained supersonic operation proves to be an exacting task which involves careful balancing of the requirements for high installed performance and system viability. The latter question may be dominated by the need to ensure flow compatibility at the intake/engine interface.

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Design and development of an air intake for a supersonic transport aircraft.

Cited by 11 publications

References 0 publications

Design Factors for Two-Dimensional, External-Compression Supersonic Inlets

Design Factors for Two-Dimensional, External-Compression Supersonic Inlets

Propulsion Integration: Supersonic Transport Aircraft

Free-Jet Testing of a Supersonic Engine/Intake Combination

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