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  • Aircraft Design, Testing and Performance  (9)
  • FLUID MECHANICS AND HEAT TRANSFER  (2)
  • 1
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    Analysis and Multipoint Design of the TCA Concept (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The goal in this effort is to analyze the baseline TCA concept at transonic and supersonic cruise, then apply the natural flow wing design concept to obtain multipoint performance improvements. Analyses are conducted with OVERFLOW, a Navier-Stokes code for overset grids, using PEGSUS to compute the interpolations between the overset grids.
    Keywords: Aircraft Design, Testing and Performance
    Type: 1997 NASA High-Speed Research Program Aerodynamic Performance Workshop; Volume 1; Part 1; 544-560; NASA/CP-1999-209691/VOL1/PT1
    Format: text
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  • 2
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    Forced Transition Techniques on HSCT Configurations (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: This presentation describes the general objectives of the project, followed by background information which led to the initiation of the study, and the approach taken to meet the objectives. Next, experimental studies in the LaRC Unitary Plan Wind Tunnel, the NMA Polysonic Wind Tunnel, and the National Transonic Facility will be discussed. Concluding remarks will close the presentation.
    Keywords: Aircraft Design, Testing and Performance
    Type: 1997 NASA High-Speed Research Program Aerodynamic Performance Workshop; Volume 1; Part 1; 477-508; NASA/CP-1999-209691/VOL1/PT1
    Format: text
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  • 3
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    The Application of the NFW Design Philosophy to the HSR Arrow Wing Configuration (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The Natural Flow Wing design philosophy was developed for improving performance characteristics of highly-swept fighter aircraft at cruise and maneuvering conditions across the Mach number range (from Subsonic through Supersonic). The basic philosophy recognizes the flow characteristics that develop on highly swept wings and contours the surface to take advantage of those flow characteristics (e.g., forward facing surfaces in low pressure regions and aft facing surfaces in higher pressure regions for low drag). Because the wing leading edge and trailing edge have multiple sweep angles and because of shocks generated on nacelles and diverters, a viscous code was required to accurately define the surface pressure distributions on the wing. A method of generating the surface geometry to take advantage of those surface pressures (as well as not violating any structural constraints) was developed and the resulting geometries were analyzed and compared to a baseline configuration. This paper will include discussions of the basic Natural Flow Wing design philosophy, the application of the philosophy to an HSCT vehicle, and preliminary wind-tunnel assessment of the NFW HSCT vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop; Pt. 2; 597-639; NASA/CP-1999-209690/PT2
    Format: text
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  • 4
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    Analysis and Inverse Design of the HSR Arrow Wing Configuration with Fuselage, Wing, and Flow Through Nacelles (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The design process for developing the natural flow wing design on the HSR arrow wing configuration utilized several design tools and analysis methods. Initial fuselage/wing designs were generated with inviscid analysis and optimization methods in conjunction with the natural flow wing design philosophy. A number of designs were generated, satisfying different system constraints. Of the three natural flow wing designs developed, the NFWAc2 configuration is the design which satisfies the constraints utilized by McDonnell Douglas Aerospace (MDA) in developing a series of optimized configurations; a wind tunnel model of the MDA designed OPT5 configuration was constructed and tested. The present paper is concerned with the viscous analysis and inverse design of the arrow wing configurations, including the effects of the installed diverters/nacelles. Analyses were conducted with OVERFLOW, a Navier-Stokes flow solver for overset grids. Inverse designs were conducted with OVERDISC, which couples OVERFLOW with the CDISC inverse design method. An initial system of overset grids was generated for the OPT5 configuration with installed diverters/nacelles. An automated regridding process was then developed to use the OPT5 component grids to create grids for the natural flow wing designs. The inverse design process was initiated using the NFWAc2 configuration as a starting point, eventually culminating in the NFWAc4 design-for which a wind tunnel model was constructed. Due to the time constraints on the design effort, initial analyses and designs were conducted with a fairly coarse grid; subsequent analyses have been conducted on a refined system of grids. Comparisons of the computational results to experiment are provided at the end of this paper.
    Keywords: Aircraft Design, Testing and Performance
    Type: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop; Pt. 2; 641-664; NASA/CP-1999-209690/PT2
    Format: text
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  • 5
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    Analysis and Multipoint Design of the TCA Concept (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The goal in this effort is to analyze the baseline TCA concept at transonic and supersonic cruise, then apply the natural flow wing design concept to obtain multipoint performance improvements. Analyses are conducted with OVERFLOW, a Navier-Stokes code for overset grids, using PEGSUS to compute the interpolations between the overset grids.
    Keywords: Aircraft Design, Testing and Performance
    Type: 1997 NASA High-Speed Research Program Aerodynamic Performance Workshop; Volume 1; Part 1; 544-560; NASA/CP-1999-209691/VOL1/PT1
    Format: text
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  • 6
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    Viscous Design of TCA Configuration (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The goal in this effort is to redesign the baseline TCA configuration for improved performance at both supersonic and transonic cruise. Viscous analyses are conducted with OVERFLOW, a Navier-Stokes code for overset grids, using PEGSUS to compute the interpolations between overset grids. Viscous designs are conducted with OVERDISC, a script which couples OVERFLOW with the Constrained Direct Iterative Surface Curvature (CDISC) inverse design method. The successful execution of any computational fluid dynamics (CFD) based aerodynamic design method for complex configurations requires an efficient method for regenerating the computational grids to account for modifications to the configuration shape. The first section of this presentation deals with the automated regridding procedure used to generate overset grids for the fuselage/wing/diverter/nacelle configurations analysed in this effort. The second section outlines the procedures utilized to conduct OVERDISC inverse designs. The third section briefly covers the work conducted by Dick Campbell, in which a dual-point design at Mach 2.4 and 0.9 was attempted using OVERDISC; the initial configuration from which this design effort was started is an early version of the optimized shape for the TCA configuration developed by the Boeing Commercial Airplane Group (BCAG), which eventually evolved into the NCV design. The final section presents results from application of the Natural Flow Wing design philosophy to the TCA configuration.
    Keywords: Aircraft Design, Testing and Performance
    Type: 1998 NASA High-Speed Research Program Aerodynamic Performance Workshop; Volume 1; Part 2; 1043-1069; NASA/CP-1999-209692/VOL1/PT2
    Format: application/pdf
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  • 7
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    Passive Control of Pressure Loads Using Porosity (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A device is provided for controlling pressure loading of a member caused by a fluid moving past the member or the member moving through a fluid. The device consists of a porous skin mounted over the solid surface of the member and separated from the solid surface by a plenum. Fluid from an area exerting high pressure on the member may enter the plenum through the porous surface and exit into an area exerting a lower pressure on the member, thus controlling pressure loading of the member.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NAS 1.71:LAR-14547-1
    Format: application/pdf
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  • 8
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    An Aerodynamic Assessment of Micro-Drag Generators (MDGs) (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Commercial transports as well as fighter aircraft of the future are being designed with very low drag (friction and pressure). Concurrently, commuter airports are being built or envisioned to be built in the centers of metropolitan areas where shorter runways and/or reduced noise footprints on takeoff and landing are required. These requirements and the fact that drag is lower on new vehicles than on older aircraft have resulted in vehicles that require a large amount of braking force (from landing-gear brakes, spoilers, high-lift flaps, thrust reversers, etc.). Micro-drag generators (MDGs) were envisioned to create a uniformly distributed drag force along a vehicle by forcing the flow to separate on the aft-facing surface of a series of deployable devices, thus, generating drag. The devices are intended to work at any speed and for any type of vehicle (aircraft, ground vehicles, sea-faring vehicles). MDGs were applied to a general aviation wing and a representative fuselage shape and tested in two subsonic wind tunnels. The results showed increases in drag of 2 to 6 times that of a "clean" configuration.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 98-2621 , 16th AIAA Applied Aerodynamics Conference; Jun 15, 1998 - Jun 18, 1998; Albuquerque, NM; United States
    Format: application/pdf
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  • 9
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    Advanced Aerodynamic Control Effectors (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A 1990 research program that focused on the development of advanced aerodynamic control effectors (AACE) for military aircraft has been reviewed and summarized. Data are presented for advanced planform, flow control, and surface contouring technologies. The data show significant increases in lift, reductions in drag, and increased control power, compared to typical aerodynamic designs. The results presented also highlighted the importance of planform selection in the design of a control effector suite. Planform data showed that dramatic increases in lift (greater than 25%) can be achieved with multiple wings and a sawtooth forebody. Passive porosity and micro drag generator control effector data showed control power levels exceeding that available from typical effectors (moving surfaces). Application of an advanced planform to a tailless concept showed benefits of similar magnitude as those observed in the generic studies.
    Keywords: Aircraft Design, Testing and Performance
    Type: Rept-1999-01-5619
    Format: application/pdf
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  • 10
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    A Discussion of Knowledge Based Design (1999)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A discussion of knowledge and Knowledge- Based design as related to the design of aircraft is presented. The paper discusses the perceived problem with existing design studies and introduces the concepts of design and knowledge for a Knowledge- Based design system. A review of several Knowledge-Based design activities is provided. A Virtual Reality, Knowledge-Based system is proposed and reviewed. The feasibility of Virtual Reality to improve the efficiency and effectiveness of aerodynamic and multidisciplinary design, evaluation, and analysis of aircraft through the coupling of virtual reality technology and a Knowledge-Based design system is also reviewed. The final section of the paper discusses future directions for design and the role of Knowledge-Based design.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 98-4944 , 7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization; Sep 02, 1998 - Sep 04, 1998; Saint Louis, MO; United States
    Format: application/pdf
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