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Development of the dual aerodynamic nozzle model for the NTF semi-span model support system

Development of the dual aerodynamic nozzle model for the NTF...

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29th AIAA Applied Aerodynamics Conference 2011

作者： Jones, Gregory S. Milholen II, William E. Goodliff, Scott L. NASA Langley Research Center Hampton VA 23681 United States Flow Physics and Control Branch Mail Stop 170 Germany Configuration Aerodynamics Branch Mail Stop 499 Germany Jacobs Technology Inc Mail Stop 267 Germany

ISBN: (纸本)9781624101458

The recent addition of a dual flow air delivery system to the NASA Langley National Transonic Facility was experimentally validated with a Dual Aerodynamic Nozzle semi-span model. This model utilized two Stratford calibration nozzles to characterize the weight flow system of the air delivery system. The weight flow boundaries for the air delivery system were identified at mildly cryogenic conditions to be 0.1 to 23 lbm/sec for the high flow leg and 0.1 to 9 lbm/sec for the low flow leg. Results from this test verified system performance and identified problems with the weight-flow metering system that required the vortex flow meters to be replaced at the end of the test. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： NASA

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Overview of the first AIAA CFD high lift prediction workshop (invited)

Overview of the first AIAA CFD high lift prediction workshop...

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49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

作者： Slotnick, Jeffrey P. Hannon, Judith A. Chaffin, Mark Boeing Company Mail Code H45N-E405 Huntington Beach CA 92647 United States Flow Physics and Control Branch Mail Stop 267 NASA Langley Research Center Hampton VA 23681-2199 United States Aerodynamics and CFD Mail Stop PAW Cessna Aircraft Company Wichita KS 67218 United States

An overview of the First AIAA CFD High Lift Prediction Workshop (HiLiftPW-1) is presented. The workshop focused on the capability of current generation Reynolds-Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) flow solvers to numerically predict the aerodynamic performance of swept, medium-to-high-aspect ratio wings in landing/take-off (high-lift) configurations. The workshop was held on June 26-27, 2010 prior to the 28 th AIAA Applied Aerodynamics Conference in Chicago, IL. The geometry configuration utilized was the National Aeronautics and Space Administration (NASA) Trapezoidal Wing (Trap Wing) high-lift wing/body geometry. The Trap Wing is a large chord, semi-span three-element configuration that was extensively tested in several NASA wind tunnels. A rich set of experimental data exists which was used in the comparisons with the CFD results. To promote consistency in CFD data comparisons and to ease the grid generation burden, several high quality, committee-generated grid systems were made available to participants. As part of the workshop, participants were encouraged to generate CFD results for a series of test cases using at least one committee-supplied grid system. If desired, participants could also create their own grid system using a specified set of grid generation guidelines. This paper describes the background and motivation for the workshop, details of the Trap Wing configuration and associated experimental data, summary of workshop test cases, and a description of the grid generation aspects of the workshop. A companion paper entitled "Summary of the First AIAA CFD High Lift Prediction Workshop" presents the CFD results, comparisons to the experimental data, and statistical analysis of the numerical results. Copyright © 2011 by J. Slotnick, J. Hannon, M. Chaffin.

关键词： Computational fluid dynamics

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Receptivity of hypersonic boundary layers over straight and flared cones

Receptivity of hypersonic boundary layers over straight and ...

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作者： Balakumar, P. Kegerise, Michael A. NASA Langley Research Center Flow Physics and Control Branch Hampton VA 23581 United States

ISBN: (纸本)9781600867392

The effects of adverse pressure gradients on the receptivity and stability of hypersonic boundary layers were numerically investigated. Simulations were performed for boundary layer flows over a straight cone and two flared cones. The steady and the unsteady flow fields were obtained by solving the two-dimensional Navier-Stokes equations in axi-symmetric coordinates using the 5th-order accurate weighted essentially non-oscillatory (WENO) scheme for space discretization and using third-order total-variation-diminishing (TVD) Runge-Kutta scheme for time integration. The mean boundary layer profiles were analyzed using local stability and non-local parabolized stability equations (PSE) methods. After the most amplified disturbances were identified, two-dimensional plane acoustic waves were introduced at the outer boundary of the computational domain and time accurate simulations were performed. The adverse pressure gradient was found to affect the boundary layer stability in two important ways. Firstly, the frequency of the most amplified second-mode disturbance was increased relative to the zero pressure gradient case. Secondly, the amplification of first- and second-mode disturbances was increased. Although an adverse pressure gradient enhances instability wave growth rates, small nose-tip bluntness was found to delay transition due to the low receptivity coefficient and the resulting weak initial amplitude of the instability waves. The computed and measured amplitude-frequency spectrums in all three cases agree very well in terms of frequency and the shape except for the amplitude.

关键词： Navier Stokes equations

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Receptivity and transition of supersonic boundary layers over swept wings

Receptivity and transition of supersonic boundary layers ove...

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作者： Balakumar, P. King, Rudolph A. Flow Physics and Control Branch NASA Langley Research Center Hampton VA 23681 United States

ISBN: (纸本)9781600867392

The receptivity, stability, and transition of three-dimensional supersonic boundary layers over (1) a swept cylinder, (2) a swept wing with a sharp leading edge, and (3) a swept wing with a blunt leading edge are numerically investigated for a free-stream Mach number of 3. These computations are compared to an earlier experimental and computational study performed by Archambaud et al.1 The steady flow fields with and without roughness elements are obtained by solving the full Navier-Stokes equations. The N-factors computed in this study at the transition onset locations reported in Ref. 1 for flow over the swept cylinder are approximately 16.5 for traveling crossflow disturbances and 9 for stationary disturbances. The N-factors for the traveling crossflow are high based on our past experiences. However, they are comparatively smaller than those reported by Archambaud et al., who found N-factor values in the range of 20 to 25 for traveling disturbances and 13 to 20 for stationary disturbances. Similarly, the N-factors computed in this study for the traveling and stationary disturbances for the flow over the sharp wing are approximately 7 and 2.5, respectively, and for the flow over the blunt wing are 6.5 and 4.8, respectively. Using the envelope method, Archambaud et al. obtained values of approximately 8.0 and 4.0 for the sharp wing case and 16.0 and 12.0 for the blunt wing case.

关键词： Swept wings

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Stability of hypersonic boundary layers on a cone at an angle of attack

Stability of hypersonic boundary layers on a cone at an angl...

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作者： Balakumar, P. Owens, Lewis R. Flow Physics and Control Branch NASA Langley Research Center Hampton VA 23681 United States MS 170 Australia

ISBN: (纸本)9781617389221

The stability and receptivity of a three-dimensional hypersonic boundary layer over a 7° half-angle straight cone at an angle of attack of 6° is numerically investigated at a free-stream Mach number of 6.0 and a Reynolds number of 10.4*106/m. The generation and evolution of stationary crossflow vortices are also investigated by performing simulations with three-dimensional roughness elements located on the surface of the cone. The flow fields with and without the roughness elements are obtained by solving the full Navier-Stokes equations in cylindrical coordinates using a fifth-order accurate weighted essentially non-oscillatory (WENO) scheme for spatial discretization and a third-order total-variation-diminishing (TVD) Runge-Kutta scheme for temporal integration. Stability computations produced azimuthal wavenumbers in the range of m ∼ 20-50 for the most amplified traveling disturbances and in the range of m ∼ 30-70 for the stationary disturbances. The frequency of the unstable second-mode ranges from 400 kHz to 900 kHz along the windward ray. The N-Factor computations predicted transition would occur more forward on the sides of the cone as compared to the transition fronts near the windward and the leeward rays. The simulations also show the crossflow vortices originating from the nose region propagate towards the leeward ray. No perturbations were observed toward the windward half of the cone.

关键词： Angle of attack

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High-speed boundary-layer transition induced by an isolated roughness element

High-speed boundary-layer transition induced by an isolated ...

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作者： Kegerise, Michael A. Owens, Lewis R. King, Rudolph A. Flow Physics and Control Branch NASA Langley Research Center Hampton VA 23681 United States M.S. 170 Australia

ISBN: (纸本)9781617389221

Progress on an experimental effort to quantify the instability mechanisms associated with roughness-induced transition in a high-speed boundary layer is reported in this paper. To simulate the low-disturbance environment encountered during high-altitude flight, the experimental study was performed in the NASA-Langley Mach 3.5 Supersonic Low-Disturbance Tunnel. A flat plate trip sizing study was performed first to identify the roughness height required to force transition. That study, which included transition onset measurements under both quiet and noisy freestream conditions, confirmed the sensitivity of roughness-induced transition to freestream disturbance levels. Surveys of the laminar boundary layer on a 7° half-angle sharp-tipped cone were performed via hot-wire anemom-etry and pitot-pressure measurements. The measured mean mass-flux and Mach-number profiles agreed very well with computed mean-flow profiles. Finally, surveys of the boundary layer developing downstream of an isolated roughness element on the cone were performed. The measurements revealed an instability in the far wake of the roughness element that grows exponentially and has peak frequencies in the 150 to 250 kHz range.

关键词： Laminar boundary layer

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Aerodynamic design of an aircraft-mounted pod for improved aero-optic performance

Aerodynamic design of an aircraft-mounted pod for improved a...

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作者： Rennie, R. Mark Crahan, Grady Jumper, Eric J. Department of Aerospace and Mechanical Engineering Center for Flow Physics and Control University of Notre Dame Notre Dame IN 46556 United States

ISBN: (纸本)9781600867392

A new approach for the shaping of pods and fairings for optical systems is presented in which the objective of the approach is to prevent or mitigate aero-optic effects. Basic streamlined shapes are developed which prevent supersonic flow and shock formation around the optical aperture. Furthermore, an innovative design for the shaping of cutouts that extend the maximum aft lookback angle of the optical system is described. The design approach is supported by computational fluid dynamic analyses, and the design of planned wind-tunnel tests is presented. © 2010 by Rennie, R.M., Crahan, G., and Jumper, E.J.

关键词： Optical systems

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Span-wise wavefront measurements through a two-dimensional weakly-compressible shear layer

Span-wise wavefront measurements through a two-dimensional w...

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作者： Ponder, Zach B. Rennie, R. Mark Abado, Shaddy Jumper, Eric J. Center for Flow Physics and Control University of Notre Dame Notre Dame IN 46554 United States Department of Aerospace and Mech. Eng. United States

ISBN: (纸本)9781600867453

Two-dimensional wavefronts were collected in the span-wise direction of a weakly-compressible two-dimensional shear layer. The measurements were made in an attempt to determine the character of the flow in the braid region between coherent structures of the convecting vortical structures. Multiple measurements were taken, including individual wavefront snapshots as well as temporally-resolved high-speed wavefronts. The individual wavefronts show the overall vertical profile of the shear layer, while the high-speed wavefront data capture the convection of the structures across the aperture. © 2010 by Ponder, Z., Rennie, R., Abado, S., and Jumper, E.

关键词： Wavefronts

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Lift enhancement by plasma actuators at low reynolds numbers

Lift enhancement by plasma actuators at low reynolds numbers

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作者： Vorobiev, Alexander Rennie, R. Mark Jumper, Eric J. Center for Flow Physics and Control University of Notre Dame Notre Dame IN 46556 United States Department of Aerospace and Mechanical Engineering United States

ISBN: (纸本)9781600867453

An experimental investigation was performed into the use of trailing-edge mounted plasma actuators for lift enhancement at low Reynolds numbers. The measurements were performed using a 0.2 m chord NACA0009 airfoil with a plasma actuator mounted at x/c = 0.75, and over the Reynolds-number range Re ∼ 70,000 to 400,000. Force-balance measurements showed that the effect of the actuator varied significantly with wind speed and angle of attack;at some test conditions, the actuator even produced a reduction in the airfoil lift. Detailed surface-pressure and LDA measurements are presented showing how the actuator flowfield interacts with the boundary layer on the airfoil trailing edge to produce the wide variation in lift enhancement effect observed in the force-balance measurements. © 2010 by Vorobiev, A., Rennie, R.M., and Jumper, E.J.

关键词： Airfoils

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Optical measurement of a compressible shear layer using a laser-induced air breakdown beacon

Optical measurement of a compressible shear layer using a la...

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作者： Rennie, R. Mark Cross, Garnett Goorskey, David Whiteley, Matthew R. Cavalieri, David Jumper, Eric J. Department of Aerospace and Mechanical Engineering Center for Flow Physics and Control University of Notre Dame Notre Dame IN 46556 United States MZA Associates Corporation Dayton OH 45459 United States

ISBN: (纸本)9781600867392

The aero-optic aberrations due to a compressible shear-layer flow with high- and low-speed Mach numbers of 0.75 and 0.12 were measured using the return light from an artificial guide star. The guide star was created by focusing a pulsed, frequency-tripled Nd:YAG laser emitting in the ultraviolet to create a laser-induced air breakdown spark. The experiments showed that accurate wavefront data could be obtained, including accurate measurements of the wavefront tip/tilt, when the shear layer was forced and the measurements were phase-locked to the forcing signal. Issues involved in integrating the beacon system into a feedforward adaptive-optic correction approach are discussed. Copyright © 2010 by Rennie, R.M., Cross, G., Goorskey, D., Whiteley, M.R., Cavalieri, D. and Jumper, E.J.

关键词： Adaptive optics

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