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  • 1
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    NASA Ames Fluid Mechanics Laboratory research briefs (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Ames Fluid Mechanics Laboratory research program is presented in a series of research briefs. Nineteen projects covering aeronautical fluid mechanics and related areas are discussed and augmented with the publication and presentation output of the Branch for the period 1990-1993.
    Keywords: AERODYNAMICS
    Type: NASA-TM-108818 , A-94073 , NAS 1.15:108818
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental investigation of turbulent flow through a circular-to-rectangular transition duct (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Steady, incompressible, turbulent, swirl-free flow through a circular-to-rectangular transition duck was studied experimentally. The cross-sectional area remains the same at the exit as at the inlet, but varies through the transition section to a maximum value approximately 15 percent above the inlet value. The cross-sectional geometry everywhere along the duct is defined by the equation of a superellipse. Mean and turbulence data were accumulated utilizing pressure and hot-wire instrumentation at five stations along the test section. Data are presented for operating bulk Reynolds numbers of 88,000 and 390,000. Measured quantities include total and static pressure, the three components of the mean velocity vector, and the six components of the Reynolds stress tensor. In addition to the transition duct measurements, a hot-wire technique which relies on the sequential use of single rotatable normal and slant-wire probes was proposed. The technique is applicable for measurement of the total mean velocity vector and the complete Reynolds stress tensor when the primary flow is arbitrarily skewed relative to a plane which lies normal to the probe axis of rotation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105210 , E-6522 , NAS 1.15:105210
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A study of transonic aerodynamic analysis methods for use with a hypersonic aircraft synthesis code (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A means of performing routine transonic lift, drag, and moment analyses on hypersonic all-body and wing-body configurations were studied. The analysis method is to be used in conjunction with the Hypersonic Vehicle Optimization Code (HAVOC). A review of existing techniques is presented, after which three methods, chosen to represent a spectrum of capabilities, are tested and the results are compared with experimental data. The three methods consist of a wave drag code, a full potential code, and a Navier-Stokes code. The wave drag code, representing the empirical approach, has very fast CPU times, but very limited and sporadic results. The full potential code provides results which compare favorably to the wind tunnel data, but with a dramatic increase in computational time. Even more extreme is the Navier-Stokes code, which provides the most favorable and complete results, but with a very large turnaround time. The full potential code, TRANAIR, is used for additional analyses, because of the superior results it can provide over empirical and semi-empirical methods, and because of its automated grid generation. TRANAIR analyses include an all body hypersonic cruise configuration and an oblique flying wing supersonic transport.
    Keywords: AERODYNAMICS
    Type: NASA-CR-189854 , NAS 1.26:189854
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Surface and flow field measurements in a symmetric crossing shock wave/turbulent boundary layer flow (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results of an experimental investigation of a symmetric crossing shock/turbulent boundary layer interaction are presented for a Mach number of 3.44 and deflections angles of 2, 6, 8 and 9 deg. The interaction strengths vary from weak to strong enough to cause a large region of separated flow. Measured quantities include surface static pressure and flowfield Pitot pressures. Pitot profiles in the plane of symmetry through the interaction region are shown for various deflection angles. Oil flow visualization and the results of a trace gas streamline tracking technique are also presented.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2634
    Format: text
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  • 5
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    Aerodynamic principles for the design of jet- engine induction systems (1956)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences
    Keywords: AERODYNAMICS
    Type: NACA-RM-A55F16
    Format: application/pdf
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  • 6
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    Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The feasibility of using a contoured honeycomb model to generate a thick boundary layer in high-speed, compressible flow was investigated. The contour of the honeycomb was tailored to selectively remove momentum in a minimum of streamwise distance to create an artificially thickened turbulent boundary layer. Three wind tunnel experiments were conducted to verify the concept. Results indicate that this technique is a viable concept, especially for high-speed inlet testing applications. In addition, the compactness of the honeycomb boundary layer simulator allows relatively easy integration into existing wind tunnel model hardware.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3142 , E-5660 , NAS 1.60:3142
    Format: application/pdf
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  • 7
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    Ethylene Trace-gas Techniques for High-speed Flows (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Three applications of the ethylene trace-gas technique to high-speed flows are described: flow-field tracking, air-to-air mixing, and bleed mass-flow measurement. The technique involves injecting a non-reacting gas (ethylene) into the flow field and measuring the concentration distribution in a downstream plane. From the distributions, information about flow development, mixing, and mass-flow rates can be dtermined. The trace-gas apparatus and special considerations for use in high-speed flow are discussed. A description of each application, including uncertainty estimates is followed by a demonstrative example.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106491 , AIAA PAPER 94-0733 , E-8478 , NAS 1.15:106491 , Aerospace Meeting and Exhibit; Jan 10, 1994 - Jan 13, 1994; Reno, NV; United States
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  • 8
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    Surface and flow field measurements in a symmetric crossing shock wave/turbulent boundary-layer interaction (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results of an experimental investigation of a symmetric crossing shock/turbulent boundary layer interaction are presented for a Mach number of 3.44 and deflection angles of 2, 6, 8, and 9 degrees. The interaction strengths vary from weak to strong enough to cause a large region of separated flow. Measured quantities include surface static pressure (both steady and unsteady) and flowfield Pitot pressures. Pitot profiles in the plane of symmetry through the interaction region are shown for various deflection angles. Oil flow visualization and the results of a trace gas streamline tracking technique are also presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106086 , E-7716 , NAS 1.15:106086 , AIAA PAPER 92-2634 , AIAA Applied Aerodynamics Conference; Jun 22, 1992 - Jun 24, 1992; Palo Alto, CA; United States
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  • 9
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    Unsteady transonic Euler solutions using finite elements (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A finite element solution of the unsteady Euler equations is presented and demonstrated for 2D airfoil configurations oscillating in transonic flows. Computations are performed by spatially discretizing the conservation equations using the Galerkin weighted residual method and then employing a multistage Runge-Kutta scheme to march forward in time. A mesh deformation scheme has been developed to efficiently move interior points in a smooth fashion as the airfoil undergoes rigid body pitch and plunge motion. Both steady and unsteady results are presented, and a comparison is made with solutions obtained using finite-volume techniques. The effects of using either a lumped or consistent mass matrix are presented; the finite element method provides an accurate solution for unsteady transonic flows about isolated airfoils.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2504 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Apr 13, 1992 - Apr 15, 1992; Dallas, TX; United States
    Format: text
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  • 10
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    Progress toward synergistic hypermixing nozzles (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Mean flow measurements were obtained for air-to-air mixing downstream of swept and unswept ramp wall mounted hypermixing nozzle configurations. Aside from the sweep of the ramps, the two nozzle configurations studied are identical. The nozzles inject three parallel supersonic jets at a 15 deg angle (relative to the wind tunnel wall) into a supersonic freestream. Mach number and volume fraction distributions in a transverse plane 11.1 nozzle heights downstream from the nozzle exit plane were measured. Data are presented for a freestream Mach number of three at a matched static pressure condition and also at underexpanded static pressure condition (pressure ratio = 5). Surface oil flow visualization was used to study the near wall flow behavior. The results indicate that the swept ramp injectors produce stronger and larger vortex pairs than the unswept ramp injectors. The increased interaction between the swept ramp model's larger vortex pairs yields better mixing characteristics for this model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105169 , E-6461 , NAS 1.15:105169 , AIAA PAPER 91-2264 , Joint Propulsion Conference; Jun 24, 1991 - Jun 27, 1991; Sacramento, CA; United States
    Format: application/pdf
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