SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 12 - JUNE 20, 2006
02 AERODYNAMICS
Includes aerodynamics of flight vehicles, test bodies, airframe components and combinations, wings, and control surfaces.
Also includes aerodynamics of rotors, stators, fans, and other elements of turbomachinery.
For related information see also 34 Fluid Mechanics and Thermodynamics.
20060014343 Texas Univ., Arlington, TX USA
DNS for Flow Separation Control Around Airfoil by Steady and Pulsed Jets
Deng, Shutian; Jiang, Li; Liu, Chaoqun; Oct 1, 2004; 43 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): F49620-01-1-0028 Report No.(s): AD-A442006; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442006; Avail.: CASI: A03, Hardcopy
No abstract available.
Airfoils; Boundary Layer Separation; Computerized Simulation; Direct Numerical Simulation; Jet Flow; Separated Flow
20060014378 Naval Undersea Warfare Center, Newport, RI USA
Modification of Vehicle Wake Vortices
Bandyopadhyay, Promode R, Inventor; Dec 9, 2005; 29 pp.; In English Report No.(s): AD-D020232; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADD020232; Avail.: CASI: A03, Hardcopy
The present invention relates to fluid dynamic forces in ships and in aeronautics. More particularly, the invention relates to vortex generation and dissipation for warship concealment and aircraft sustentation by movably mounted hull adjunct or fluid introducing elements. DTIC
Fluid Dynamics; Patent Applications; Vortex Generators; Vortices; Wakes
20060014414 Office National d'Etudes et de Recherches Aerospatiales, Toulouse, France
Control of Separated Flows and Buffeting in Transonic Flow
Caruana, D; Mignosi, A; Correge, M; Le Pourhiet, A; Oct 1, 2004; 21 pp.; In English; Original contains color illustrations Report No.(s): AD-A442052; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442052; Avail.: CASI: A03, Hardcopy
No abstract available
Aerodynamic Characteristics; Buffeting; Separated Flow; Stability; Transonic Flow
20060014442 Georgia Inst. of Tech., Atlanta, GA USA
Fluidic-Based Virtual Aerosurface Shaping
Glezer, Ari; Oct 1, 2004; 20 pp.; In English; Original contains color illustrations Report No.(s): AD-A442182; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442182; Avail.: CASI: A03, Hardcopy
No abstract available
Boundary Layer Flow; Boundary Layer Transition; Fluidics; Lift; Shapes
SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS A Biweekly Publication of the National Aeronautics and Space Administration VOLUME 44, JUNE 20, 2006
20060014447 Iowa State Univ. of Science and Technology, Ames, IA USA
Separation and Unsteady Vortex Shedding from Leading Edge Surface Roughness
Matheis, B D; Huebsch, W W; Rothmayer, A P; Oct 1, 2004; 25 pp.; In English; Original contains color illustrations Report No.(s): AD-A442193; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442193; Avail.: CASI: A03, Hardcopy
No abstract available
Airfoils; Boundary Layer Separation; Leading Edges; Separated Flow; Surface Roughness; Unsteady Flow; Vortex Shedding
20060014724 Guided Systems Technologies, McDonough, GA USA
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Neural Network Based Adaptive Flow Control for Maneuvering Vehicles
Corban, J E; Glezer, An; Calise, Anthony; Sep 2005; 34 pp.; In English Contract(s)/Grant(s): FA9550-04-C-0075 Report No.(s): AD-A442369; GST-FA9550-03; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442369; Avail.: CASI: A03, Hardcopy
This report documents a phase I STIR effort with the objective of developing and demonstrating effective nonlinear adaptive control of the aerodynamic flow about a dynamic body using a distributed array of synthetic jets for actuation. Design of a wind-tunnel test apparatus is presented. Motion of the model is constrained to two degrees of freedom. A conventional elevator is used to trim the model and change its dynamic characteristics. Position control of the model is achieved by an adaptive outer loop controller. This outer loop commands the flow control actuators. A dynamic simulation model of the wind tunnel apparatus is presented, as are designs for both the inner and outer loop controllers. The outer loop design is adaptive. Anon-minimum phase transfer function is presented to model the active flow control actuators, and includes possible coupling effects between actuation, the dynamics of flow field, and the rigid body dynamics of the model. The outcomes of simulation studies are presented. The parameters were selected to have an adverse effect on the closed loop response, therefore representing a hypothetical worst-case situation. These results demonstrate successful adaptive control of the simulated wind tunnel test article employing flow devices for actuation. DTIC
Adaptive Control; Maneuvers; Network Control; Neural Nets; Wind Tunnel Tests
20060014730 Illinois Inst. of Tech., Chicago, IL USA
First-In-Flight Full-Scale Application of Active Flow Control: The XV-15 Tiltrotor Download Reduction
Nagib, Hassan M; Kiedaisch, John W; Wygnanski, Israel J; Stalker, Aaron D; Wood, Tom; McVeigh, Michael A; Oct 1, 2004; 37 pp.; In English; Original contains color illustrations Report No.(s): AD-A442393; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442393; Avail.: CASI: A03, Hardcopy
No abstract available
Boundary Layer Separation; Drag Reduction; Flight Tests; Hovering; Separated Flow; Tilt Rotor Aircraft; XV-15 Aircraft
20060014735 Arizona State Univ., Tempe, AZ USA
Flight Testing of Laminar Flow Control in High-Speed Boundary Layers
Saric, William S; Reed, Helen L; Banks, Daniel W; Oct 1, 2004; 9 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): MDA972-01-2-0001 Report No.(s): AD-A442442; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442442; Avail.: CASI: A02, Hardcopy
No abstract available
Boundary Layer Control; Boundary Layer Separation; Boundary Layers; Drag Reduction; Fighter Aircraft; Flight Tests; High Speed; Jet Aircraft; Laminar Boundary Layer; Laminar Flow; Separated Flow
20060014755 Technische Univ., Brunswick, Germany
RANS Simulation of the Transitional Flow Around Airfoils at Low Reynolds Numbers for Steady and Unsteady Onset Conditions
Windte, Jan; Radespiel, Rolf; Scholz, Ulrich; Eisfeld, Bernhard; Oct 1, 2004; 21 pp.; In English; Original contains color illustrations Report No.(s): AD-A442472; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442472; Avail.: CASI: A03, Hardcopy
No abstract available
Aerodynamic Characteristics; Airfoils; Laminar Flow; Low Reynolds Number; Navier-Stokes Equation; Reynolds Number; Simulation; Transition Flow; Turbulent Flow
20060014775 London Univ., UK
A Rapid Method of Calculating N-Factors for Estimating Transition Position
Gaster, M; Oct 1, 2004; 13 pp.; In English; Original contains color illustrations Report No.(s): AD-A442628; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442628; Avail.: CASI: A03, Hardcopy
No abstract available
Airfoils; Boundary Layer Transition; Compressible Flow; Computational Fluid Dynamics; Eigenvalues; Estimating
20060014831 Technische Hochschule, Stuttgart, Germany
Interaction of Separation and Transition in Laminar Separation Bubbles in a 3D-Boundary Layer
Hetsch, T; Rist, U; Oct 1, 2004; 13 pp.; In English; Original contains color illustrations Report No.(s): AD-A442729; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442729; Avail.: CASI: A03, Hardcopy
No abstract available
Boundary Layer Flow; Boundary Layer Separation; Boundary Layer Transition; Boundary Layers; Bubbles; Laminar Flow; Separated Flow
20060014858 University of Western Ontario, London, Ontario Canada
Stability of Shear Layers over Rough Surfaces
Floryan, J M; Oct 1, 2004; 11 pp.; In English; Original contains color illustrations Report No.(s): AD-A442776; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442776; Avail.: CASI: A03, Hardcopy
No abstract available
Aerodynamic Stability; Boundary Layer Transition; Shear Flow; Shear Layers; Stability; Surface Roughness
20060015447 Army Research Lab., Adelphi, MD USA
Evaluation of Microphone Windscreen Performance in a Wind Tunnel
Tran-Luu, Tung-Duong; Solomon, Latasha; Dec 2005; 32 pp.; In English Report No.(s): AD-A443313; ARL-MR-0636; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443313; Avail.: CASI: A03, Hardcopy
Turbulent wind noise can severely degrade acoustic signals often making it difficult to detect classify and/or track signals of interest. Windscreens are often used to suppress such noise. This research compares the effectiveness of various windscreens to suppress wind noise while tested in a controlled environment. DTIC
Aerodynamic Noise; Microphones; Signal Transmission; Sound Waves; Wind Tunnel Tests; Wind Tunnels; Windshields
20060015615 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
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C-17 Centerlining - Analysis of Paratrooper Trajectory
Barnes, Waldemar F; Jun 2005; 59 pp.; In English; Original contains color illustrations Report No.(s): AD-A441525; AFIT/GOS/ENS/05-02; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA441525; Avail.: CASI: A04, Hardcopy
The C-17's widebody design creates concern over its tendency to 'centerline' paratroopers as they exit. This effect increases the probability of collision between jumpers from opposite sides of the aircraft.
Previous work has been accomplished based on calculating the separation distance between trajectories and creating cumulative distributions of separation distances.
This project focuses its analysis on the trajectories and any trends that can be seen over time, based on changing aircraft gross weight. The trajectories are also analyzed for time dependence.
In the end, new insight is gained into the behavior of the trajectories and can supplement previous efforts with additional methodology. DTIC
Trajectories; C-17 Aircraft
Source: NASA
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