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  • 1
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    Preliminary Comparison of Skin Friction Measurements with CFD Predictions (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The work to be described was performed at the NASA Langley UPWT (4-ft supersonic), test section #2, during 21-24 May 1996. The configuration being tested was the 1.675% Ref H controls model; test conditions were Ma = 2.40, Re = 3 million/ft. This was an exploration of a new technique, and it was not intended to provide definitive comparison of measured and computed skin friction results. It is, however, hoped that the experience gained will make such a rigorous comparison possible in the future.
    Keywords: Aerodynamics
    Type: 1997 NASA High-Speed Research Program Aerodynamic Performance; Volume 1; Part 2; 1478-1499; NASA/CP-1999-209691/VOL1/PT2
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Drag measurements of an axisymmetric nacelle mounted on a flat plate at supersonic speeds (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the effect of diverter wedge half-angle and nacelle lip height on the drag characteristics of an assembly consisting of a nacelle fore cowl from a typical high-speed civil transport (HSCT) and a diverter mounted on a flat plate. Data were obtained for diverter wedge half-angles of 4.0 deg, 6.0 deg, and 8.0 deg and ratios of the nacelle lip height above a flat plate to the boundary-layer thickness (h(sub n)/delta) of approximately 0.87 to 2.45. Limited drag data were also obtained on a complete nacelle/diverter configuration that included fore and aft cowls. Although the nacelle/diverter drag data were not corrected for base pressures or internal flow drag, the data are useful for comparing the relative drag of the configuration tested. The tests were conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.50, 1.80, 2.10, and 2.40 and Reynolds numbers ranging from 2.00 x 10(exp 6) to 5.00 x 10(exp 6) per foot. The results of this investigation showed that the nacelle/diverter drag essentially increased linearly with increasing h(sub n)/delta except near 1.0 where the data showed a nonlinear behavior. This nonlinear behavior was probably caused by the interaction of the shock waves from the nacelle/diverter configuration with the flat-plate boundary layer. At the lowest h(sub n)/delta tested, the diverter wedge half-angle had virtually no effect on the nacelle/diverter drag. However, as h(sub n)/delta increased, the nacelle/diverter drag increased as diverter wedge half-angle increased.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4660 , L-17416 , NAS 1.15:4660
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Supersonic aerodynamic characteristics of a Mach 3 high-speed civil transport configuration (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NASA-Langley AST31 high-speed civil transport (HSCT) configuration, a blended wing/fuselage concept scaled for 250-passenger carriage over 6500 nmi, has been subjected to both CFD and wind tunnel tests; the wind tunnel tests were conducted in the Mach 1.6-3.6 range. The inability of the linear theory method to accurately predict stability levels as well as nonlinear pitching moment characteristics demonstrates the need to undertake high-order analyses as early in the design process as possible. An HSCT laminar flow capability experimental study was conducted in order to simulate 50-percent laminar flow conditions, and thereby ascertain the difference in drag relative to fully turbulent conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-3210
    Format: text
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  • 4
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    Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A static experimental investigation of a counterflow thrust vectoring nozzle concept was performed. The study was conducted in the NASA Langley Research Center Jet Exit Test Facility. Internal performance characteristics were defined over a nozzle pressure ratio (jet total to ambient) range of 3.5 to 10.0. The effects of suction collar geometry and suction slot height on nozzle performance were examined. In the counterflow concept, thrust vectoring is achieved by applying a vacuum to a slot adjacent to a primary jet that is shrouded by a suction collar. Two flow phenomena work to vector the primary jet depending upon the test conditions and configuration. In one case, the vacuum source creates a secondary reverse flowing stream near the primary jet. The shear layers between the two counterflowing streams mix and entrain mass from the surrounding fluid. The presence of the collar inhibits mass entrainment and the flow near the collar accelerates, causing a drop in pressure on the collar. The second case works similarly except that the vacuum is not powerful enough to create a counterflowing stream and instead a coflowing stream is present. The primary jet is vectored if suction is applied asymmetrically on the top or bottom of the jet.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA Paper 98-3255 , 34th AIAA/ASME SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 13, 1998 - Jul 15, 1998; Cleveland, OH; United States
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  • 5
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    Status of ERA Vehicle System Integration Technology Demonstrators (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Acoustics; Aerodynamics
    Type: NF1676L-20528 , AIAA SciTech 2015; Jan 05, 2015 - Jan 08, 2015; Kissimmee, FL; United States
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  • 6
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    Status of ERA Vehicle System Integration Technology Demonstrators (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Environmentally Responsible Aviation (ERA) Project within the Integrated Systems Research Program (ISRP) of the NASA Aeronautics Research Mission Directorate (ARMD) has the responsibility to explore and document the feasibility, benefits, and technical risk of air vehicle concepts and enabling technologies that will reduce the impact of aviation on the environment. The primary goal of the ERA Project is to select air vehicle concepts and technologies that can simultaneously reduce fuel burn, noise, and emissions. In addition, the ERA Project will identify and mitigate technical risk and transfer knowledge to the aeronautics community at large so that new technologies and vehicle concepts can be incorporated into the future design of aircraft.
    Keywords: Aerodynamics
    Type: NF1676L-19361 , SciTech; Jan 05, 2015 - Jan 09, 2015; Kissimmee, Fl; United States
    Format: application/pdf
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  • 7
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    Some Reflections on Aerodynamic Force And Moment Testing (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance; Aerodynamics
    Type: NF1676L-28161 , Propulsion Airframe Integration Testing Seminar; Apr 17, 2017; Hampton, VA; United States
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  • 8
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    Active Tailoring of Lift Distribution to Enhance Cruise Performance (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: During Phase I of this project, Raytheon Aircraft Company (RAC) has analytically and experimentally evaluated key components of a system that could be implemented for active tailoring of wing lift distribution using low-drag, trailing-edge modifications. Simple systems such as those studied by RAC could be used to enhance the cruise performance of a business jet configuration over a range of typical flight conditions. The trailing-edge modifications focus on simple, deployable mechanisms comprised of extendable small flap panels over portions of the span that could be used to subtly but positively optimize the lift and drag characteristics. The report includes results from low speed wind tunnel testing of the trailing-edge devices, descriptions of potential mechanisms for automation, and an assessment of the technology.
    Keywords: Aerodynamics
    Type: NASA/CR-2005-213543 , CONE181952
    Format: application/pdf
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  • 9
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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
    Format: application/pdf
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  • 10
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    Computational Study of Fluidic Thrust Vectoring using Separation Control in a Nozzle (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A computational investigation of a two- dimensional nozzle was completed to assess the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. The nozzle was designed with a recessed cavity to enhance the throat shifting method of fluidic thrust vectoring. The structured-grid, computational fluid dynamics code PAB3D was used to guide the design and analyze over 60 configurations. Nozzle design variables included cavity convergence angle, cavity length, fluidic injection angle, upstream minimum height, aft deck angle, and aft deck shape. All simulations were computed with a static freestream Mach number of 0.05. a nozzle pressure ratio of 3.858, and a fluidic injection flow rate equal to 6 percent of the primary flow rate. Results indicate that the recessed cavity enhances the throat shifting method of fluidic thrust vectoring and allows for greater thrust-vector angles without compromising thrust efficiency.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2003-3803 , The 21st AlAA Applied Aerodynamics Conference; Jun 23, 2003 - Jun 26, 2003; Orlando, FL; United States
    Format: application/pdf
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