A New Design Concept for Supersonic Axisymmetric Inlets

Weir, Lois J.; Sanders, B. W.; Vachon, Jake

doi:10.2514/6.2002-3775

Cited by 9 publications

(6 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…5 The present study extends these computational results by using an axisymmetric geometry that is more accurate to the flight hardware.…”

mentioning

confidence: 67%

Analysis of a Channeled Centerbody Supersonic Inlet for F-15B Flight Research

Ratnayake

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

The Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center is a unique test platform available for use on the NASA F-15B airplane, tail number 836, as a modular host for a variety of aerodynamics and propulsion research. The first experiment that is to be flown on the test fixture is the Channeled Centerbody Inlet Experiment. The objectives of this project at Dryden are twofold: 1) flight evaluation of an innovative new approach to variable geometry for high-speed inlets, and 2) flight validation of channeled inlet performance prediction by complex computational fluid dynamics codes. The inlet itself is a fixed-geometry version of a mixed-compression, variable-geometry, supersonic inlet developed by TechLand Research, Inc. (North Olmsted, Ohio) to improve the efficiency of supersonic flight at off-nominal conditions. The concept utilizes variable channels in the centerbody section to vary the mass flow of the inlet, enabling efficient operation at a range of flight conditions. This study is particularly concerned with the starting characteristics of the inlet. Computational fluid dynamics studies were shown to align well with analytical predictions, showing the inlet to remain unstarted as designed at the primary test point of Mach 1.5 at an equivalent pressure altitude of 29,500 ft local conditions. Mass-flow-related concerns such as the inlet start problem, as well as inlet efficiency in terms of total pressure loss, are assessed using the flight test geometry.

show abstract

“…5 The present study extends these computational results by using an axisymmetric geometry that is more accurate to the flight hardware.…”

mentioning

confidence: 67%

Analysis of a Channeled Centerbody Supersonic Inlet for F-15B Flight Research

Ratnayake

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…I y and I z were found using the solid model created in Solidworks to be I y = 0.20127767 in 4 and I z = 0.00600179 in 4 . A short numerical routine was written that determines the maximum normal stress in the rake.…”

Section: Analytical Calculations Of Rake Stressmentioning

confidence: 99%

“…The Cone Drag Experiment, in which the cylinder with conical nosecap assembly was tested in order to validate the PFTF's integral six-axis force balance .3 The next experiment planned for the PFTF is the flight test of the Channeled Centerbody Inlet Experiment (CCIE); 4 however, for the flight data from this test to be valid, more information is required to quantify the quality of the airflow through the aerodynamic interface plane of the inlet, which is the plane facing into the airflow at the planned location of the tip of the inlet centerbody. The flow angularity and Mach number must be known at multiple locations on the interface plane.…”

Section: Introductionmentioning

confidence: 99%

Design and Calibration of a Flowfield Survey Rake for Inlet Flight Research

Flynn

Ratnayake

Frederick

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

The Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center is a unique test platform available for use on NASA's F-15B aircraft, tail number 836, as a modular host for a variety of aerodynamics and propulsion research. For future flight data from this platform to be valid, more information must be gathered concerning the quality of the airflow underneath the body of the F-15B at various flight conditions, especially supersonic conditions. The flow angularity and Mach number must be known at multiple locations on any test article interface plane for measurement data at these locations to be valid. To determine this prerequisite information, flight data will be gathered in the Rake Airflow Gauge Experiment using a custom-designed flowfield rake to probe the airflow underneath the F-15B at the desired flight conditions. This paper addresses the design considerations of the rake and probe assembly, including the loads and stress analysis using analytical methods, computational fluid dynamics, and finite element analysis. It also details the flow calibration procedure, including the completed wind-tunnel test and posttest data reduction, calibration verification, and preparation for flight-testing. = total pressure at probe n total pressure port, psf q = dynamic pressure, psf RAGE = Rake Airflow Gauge Experiment T t = wind tunnel or CFD total temperature, °R x = distance from centroid along x-axis, in. y = distance from centroid along y-axis, in. z = distance from centroid along z-axis, in. 2D = two-dimensional 3D = three-dimensional α = angle of attack, deg β = angle of sideslip, deg βq = product of sideslip angle and dynamic pressure β b = body axis angle of sideslip, deg β t = true angle of sideslip, deg δ 0 = wind-tunnel horizontal bias (misalignment) angle, deg θ = probe pitch angle (wind-tunnel), deg θ n = probe pitch angle corrected for bias, deg θ 0 = wind-tunnel pitch bias (misalignment) angle, deg σ n = normal stress, ksi σ x = normal stress, psi σ xx,max = maximum axial stress, ksi σ yield = yield stress, ksi φ = probe roll angle (wind-tunnel), deg φ n = probe roll angle corrected for bias, deg 3

show abstract

“…In this study we are particularly concerned with the effects of channels, so the translating of centerbody is beyond the scope of our study. The bottom of channels can be simply composed of a slant and a floor [1], but the area distribution of the inlet changes abruptly, and the position of the throat of the channels is unstable during the closing down process. We developed a design method to determine the channel contour which can keep the location of the channel stably during closing down process.…”

Section: Introductionmentioning

confidence: 99%

“…The variable diameter centerbody inlet is very complex. Weir, L. J [1] developed a new design concept for supersonic axisymmetric inlets. This variable geometry system opens up longitudinal channels in the centerbody with forward centerbody translation at off design Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

Research on the Design Methods of Channeled Centerbody Supersonic Inlet

Tongguang

Wang

2015

Procedia Engineering

View full text Add to dashboard Cite

Channeling centerbody provides a wide variation in throat area, which makes it possible to start the inlet at lower velocity and get high performance at cruise conditions. We developed a new method to design the channels and performed three-dimensional computational fluid dynamics analysis. We found that the starting characteristics of the channeled centerbody inlet are different from that of the equivalent centerbody inlet The unchanneled parts of the inlet are still unstarted at low Mach numbers, and the aerodynamic performance of the channeled parts of the inlet are apparently affected by the channels. Boundary layer separation developed seriously due to abruptly turning down of the channel contour, and it decreased the available cross-section area of the channel seriously.

show abstract

A New Design Concept for Supersonic Axisymmetric Inlets

Cited by 9 publications

References 0 publications

Analysis of a Channeled Centerbody Supersonic Inlet for F-15B Flight Research

Analysis of a Channeled Centerbody Supersonic Inlet for F-15B Flight Research

Design and Calibration of a Flowfield Survey Rake for Inlet Flight Research

Research on the Design Methods of Channeled Centerbody Supersonic Inlet

Contact Info

Product

Resources

About