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  • FLUID MECHANICS AND HEAT TRANSFER  (3.305)
  • AERODYNAMICS  (2.823)
  • 1990-1994  (6.128)
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  • 1
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    2-D and 3-D oscillating wing aerodynamics for a range of angles of attack including stall (1994)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A comprehensive experimental investigation of the pressure distribution over a semispan wing undergoing pitching motions representative of a helicopter rotor blade was conducted. Testing the wing in the nonrotating condition isolates the three-dimensional (3-D) blade aerodynamic and dynamic stall characteristics from the complications of the rotor blade environment. The test has generated a very complete, detailed, and accurate body of data. These data include static and dynamic pressure distributions, surface flow visualizations, two-dimensional (2-D) airfoil data from the same model and installation, and important supporting blockage and wall pressure distributions. This body of data is sufficiently comprehensive and accurate that it can be used for the validation of rotor blade aerodynamic models over a broad range of the important parameters including 3-D dynamic stall. This data report presents all the cycle-averaged lift, drag, and pitching moment coefficient data versus angle of attack obtained from the instantaneous pressure data for the 3-D wing and the 2-D airfoil. Also presented are examples of the following: cycle-to-cycle variations occurring for incipient or lightly stalled conditions; 3-D surface flow visualizations; supporting blockage and wall pressure distributions; and underlying detailed pressure results.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-4632 , A-94053 , NAS 1.15:4632 , USAATCOM-TR-94-A-011
    Format: application/pdf
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  • 2
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    2nd NASA CFD Validation Workshop (1990)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The purpose of the workshop was to review NASA's progress in CFD validation since the first workshop (held at Ames in 1987) and to affirm the future direction of the NASA CFD validation program. The first session consisted of overviews of CFD validation research at each of the three OAET research centers and at Marshall Space Flight Center. The second session consisted of in-depth technical presentations of the best examples of CFD validation work at each center (including Marshall). On the second day the workshop divided into three working groups to discuss CFD validation progress and needs in the subsonic, high-speed, and hypersonic speed ranges. The emphasis of the working groups was on propulsion.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-TM-107972 , NAS 1.15:107972 , 2nd NASA CFD Validation Workshop; Jul 10, 1990 - Jul 12, 1990; Cleveland, OH; United States
    Format: application/pdf
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  • 3
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    3-D Euler calculations for aft-propfan integration (1990)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The problem of reducing engine-airframe installation drag for a transport aircraft with an aft-mounted propfan or turboprop engine is investigated. A three-dimensional Euler code is used for the analysis. Installation drag effects are inferred from a qualitative analysis of the computed velocity and pressure distributions. The basic design philosophy is to alleviate flow acceleration near the strut/nacelle junction by aerodynamic means. This involves minor reshaping and relocation of the propulsion system.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 90-2147
    Format: text
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  • 4
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    3-D Navier-Stokes analysis of crossing, glancing shocks/turbulent boundary layer interactions (1991)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: Three dimensional viscous flow analysis is performed for a configuration where two crossing and glancing shocks interact with a turbulent boundary layer. A time marching 3-D full Navier-Stokes code, called PARC3D, is used to compute the flow field, and the solution is compared to the experimental data obtained at the NASA Lewis Research Center's 1 x 1 ft supersonic wind tunnel facility. The study is carried out as part of the continuing code assessment program in support of the generic hypersonic research at NASA Lewis. Detailed comparisons of static pressure fields and oil flow patterns are made with the corresponding solution on the wall containing the shock/boundary layer interaction in an effort to validate the code for hypersonic inlet applications.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 91-1758
    Format: text
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  • 5
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    3-D viscous flow CFD analysis of the propeller effect on an advanced ducted propeller subsonic inlet (1993)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The time-marching Navier-Stokes code PARC3D was used to study the 3D viscous flow associated with an advanced ducted propeller subsonic inlet at take-off operating conditions. At a free stream Mach number of 0.2, experimental data for the inlet-with-propeller test model indicated that the airflow was attached on the cowl windward lip at an angle of attack of 25 deg became unstable at 29 deg, and separated at 30 deg. An experimental study with a similar inlet and without propeller (through-flow) indicated that flow separation occurred at an angle of attack a few degrees below the value observed when the inlet was tested with the propeller, indicating the propeller's favorable effect on inlet performance. In the present numerical study, flow blockage analogous to the propeller was modeled via a PARC3D computational boundary condition (BC), the 'screen BC', based on 1-1/2 dimension actuator disk theory. The application of the screen BC in this numerical study provided results similar to those of past experimental efforts in which either the blockage device or the propeller was used.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 93-1847 , AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States|; 40 p.
    Format: text
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  • 6
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    30 degree injectors at hypervelocity conditions (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Results are presented of the first high-speed propulsion-related experiments performed in the NASA-Ames 16-Inch Shock Tunnel, designed to simulate combustor inlet conditions at approximately Mach 14. Results demonstrate the capability of the tunnel for high-speed propulsion testing and yield data on the performance of 30-deg flush wall injectors tested in the tunnel. The experimental results are compared with those of a CFD analysis.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 92-3288
    Format: text
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  • 7
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    3D automatic Cartesian grid generation for Euler flows (1993)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: We describe a Cartesian grid strategy for the study of three dimensional inviscid flows about arbitrary geometries that uses both conventional and CAD/CAM surface geometry databases. Initial applications of the technique are presented. The elimination of the body-fitted constraint allows the grid generation process to be automated, significantly reducing the time and effort required to develop suitable computational grids for inviscid flowfield simulations.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 93-3386 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 2 (A93-44994 18-34); p. 959-969.
    Format: text
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  • 8
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    3D computation of hypersonic nozzle (1990)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Numerical results of a NASP-like nozzle configuration are presented. The nozzle has characteristically a very large area ratio designed to operate in the hypersonic regime. The overall flowfield consists of the internal expansion from a stagnation reservoir and the external exhaust plume in a quiescent environment. The solutions were obtained for two experimental conditions at an underexpanded pressure ratio of 44000 and an overexpanded pressure ratio of 2495. These conditions produce flows expanding to high Mach numbers in the hypersonic range. At the nozzle entrance, the flow has a supersonic Mach number of 4.3 in the inviscid region. In the external expansion and exhaust regions, the flow expands to a maximum Mach number of 12.3 for the case of high pressure ratio, whereas a shock wave exists for the low pressure ratio case. The solutions from these three-dimensional calculations were compared to the experimental data for pressure distributions.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 90-5203
    Format: text
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  • 9
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    3D Euler analysis of ducted propfan flowfields (1990)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A numerical method is presented for predicting the steady inviscid flow through a ducted propfan based on a time-marching solution of the three-dimensional Euler equations. A four-stage multiple-block Runge-Kutta finite volume numerical technique, utilizing implicit residual smoothing and a blended second and fourth difference dissipation, is applied to predict the transonic flowfield about both single-rotation and counter-rotations ducted rotors. Counter-rotation predictions are based on an average-passage system of equations approach. Calculations are performed for both a single sheared H-type grid system and a multiple-block grid system incorporating a C-type grid about the cowl. Numerical results are compared with experimental data for two cases: a low speed ducted propeller and a 1.15 pressure ratio fan stage.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 90-3034 , AIAA Applied Aerodynamics Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: text
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  • 10
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    3D Euler flow solutions using unstructured Cartesian and prismatic grids (1993)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A hyperbolic prismatic grid generation technique is combined with a background Cartesian grid for the study of inviscid three-dimensional flows. The mathematics of the hyperbolic prismatic grid generation algorithm are described, and some simple inviscid demonstration cases are presented. By combining the simplicity of the Cartesian background grid with the geometric flexibility and computational efficiencies inherent to prismatic grids, this approach shows promise for improving computational aerodynamic simulations.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 93-0331 , ; 12 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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