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  • 1
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    Vortex Flows at Supersonic Speeds (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A review of research conducted at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) into high-speed vortex flows during the 1970s, 1980s, and 1990s is presented. The data are for flat plates, cavities, bodies, missiles, wings, and aircraft with Mach numbers of 1.5 to 4.6. Data are presented to show the types of vortex structures that occur at supersonic speeds and the impact of these flow structures on vehicle performance and control. The data show the presence of both small- and large-scale vortex structures for a variety of vehicles, from missiles to transports. For cavities, the data show very complex multiple vortex structures exist at all combinations of cavity depth to length ratios and Mach number. The data for missiles show the existence of very strong interference effects between body and/or fin vortices. Data are shown that highlight the effect of leading-edge sweep, leading-edge bluntness, wing thickness, location of maximum thickness, and camber on the aerodynamics of and flow over delta wings. Finally, a discussion of a design approach for wings that use vortex flows for improved aerodynamic performance at supersonic speeds is presented.
    Keywords: Aerodynamics
    Type: NASA/TP-2003-211950 , L-18008 , NAS 1.60:211950
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Base Passive Porosity for Drag Reduction (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A device for controlling drag on a ground vehicle. The device consists of a porous skin mounted on the trailing surface of the ground vehicle. The porous skin may be separated from the vehicle surface by a distance of at least the thickness of the porous skin. Alternately, the trailing surface of the ground vehicle may be porous. The device minimizes the strength of the separation in the base and wake regions of the ground vehicle, thus reducing drag.
    Keywords: Aerodynamics
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Base passive porosity for vehicle drag reduction (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A device for controlling drag on a ground vehicle. The device consists of a porous skin or skins mounted on the trailing surface and/or aft portions of the ground vehicle. The porous skin is separated from the vehicle surface by a distance of at least the thickness of the porous skin. Alternately, the trailing surface, sides, and/or top surfaces of the ground vehicle may be porous. The device minimizes the strength of the separation in the base and wake regions of the ground vehicle, thus reducing drag.
    Keywords: Aerodynamics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic Design Opportunities for Future Supersonic Aircraft (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A discussion of a diverse set of aerodynamic opportunities to improve the aerodynamic performance of future supersonic aircraft has been presented and discussed. These ideas are offered to the community in a hope that future supersonic vehicle development activities will not be hindered by past efforts. A number of nonlinear flow based drag reduction technologies are presented and discussed. The subject technologies are related to the areas of interference flows, vehicle concepts, vortex flows, wing design, advanced control effectors, and planform design. The authors also discussed the importance of improving the aerodynamic design environment to allow creativity and knowledge greater influence. A review of all of the data presented show that pressure drag reductions on the order of 50 to 60 counts are achievable, compared to a conventional supersonic cruise vehicle, with the application of several of the discussed technologies. These drag reductions would correlate to a 30 to 40% increase in cruise L/D (lift-to-drag ratio) for a commercial supersonic transport.
    Keywords: Aerodynamics
    Type: ICAS-2002-8.7.1(I.L.) , 23rd International Congress of Aeronautical Sciences; Sep 08, 2002 - Sep 13, 2002; Toronto; Canada
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  • 5
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    Advanced Aerodynamic Design of Passive Porosity Control Effectors (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes aerodynamic design work aimed at developing a passive porosity control effector system for a generic tailless fighter aircraft. As part of this work, a computational design tool was developed and used to layout passive porosity effector systems for longitudinal and lateral-directional control at a low-speed, high angle of attack condition. Aerodynamic analysis was conducted using the NASA Langley computational fluid dynamics code USM3D, in conjunction with a newly formulated surface boundary condition for passive porosity. Results indicate that passive porosity effectors can provide maneuver control increments that equal and exceed those of conventional aerodynamic effectors for low-speed, high-alpha flight, with control levels that are a linear function of porous area. This work demonstrates the tremendous potential of passive porosity to yield simple control effector systems that have no external moving parts and will preserve an aircraft's fixed outer mold line.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-0249 , Aerospace Sciences; Jan 08, 2001 - Jan 11, 2001; Reno, NV; United States
    Format: application/pdf
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  • 6
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    Flying wings / flying fuselages (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The present paper has documented the historical relationships between various classes of all lifting vehicles, which includes the flying wing, all wing, tailless, lifting body, and lifting fuselage. The diversity in vehicle focus was to ensure that all vehicle types that map have contributed to or been influenced by the development of the classical flying wing concept was investigated. The paper has provided context and perspective for present and future aircraft design studies that may employ the all lifting vehicle concept. The paper also demonstrated the benefit of developing an understanding of the past in order to obtain the required knowledge to create future concepts with significantly improved aerodynamic performance.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-0311 , Aerospace Sciences; Jan 08, 2001 - Jan 11, 2001; Reno, NV; United States
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  • 7
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    On the Use of Surface Porosity to Reduce Unsteady Lift (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An innovative application of existing technology is proposed for attenuating the effects of transient phenomena, such as rotor-stator and rotor-strut interactions, linked to noise and fatigue failure in turbomachinery environments. A computational study was designed to assess the potential of passive porosity technology as a mechanism for alleviating interaction effects by reducing the unsteady lift developed on a stator airfoil subject to wake impingement. The study involved a typical high bypass fan Stator airfoil (solid baseline and several porous configurations), immersed in a free field and exposed to the effects of a transversely moving wake. It was found that, for the airfoil under consideration, the magnitude of the unsteady lift could be reduced more than 18% without incurring significant performance losses.
    Keywords: Aerodynamics
    Type: AIAA Paper 2001-2921 , 31st AIAA Fluid Dynamics Conference and Exhibit; Jun 11, 2001 - Jun 14, 2001; Anaheim, CA; United States
    Format: application/pdf
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