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  • AERODYNAMICS  (12,790)
  • FLUID MECHANICS AND HEAT TRANSFER
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  • 1
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    1963- THE GREATEST YEAR IN SPACE (1963)
    In:  Other Sources
    Details
    Publication Date: 2011-08-10
    Description: Proposed space program for 1963-1964 period, including manned and unmanned space investigation, space applications and advanced research
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 2
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    1989 Computational Fluid Dynamics Highlights (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This video presents highlights of 1989's CFD graphics, which show shuttle flight problems, F-18 flows, artificial heart, and rotorstrator with more complex blades.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ARC-AAV-1289 , NASA-TM-109635 , NONP-NASA-VT-93-190433
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    NASA TECHNICAL REPORTS
  • 3
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    2-D and 3-D mixing flow analyses of a scramjet-afterbody configuration (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A cold simulant gas study of propulsion/airframe integration for a hypersonic vehicle powered by a scramjet engine is presented. The specific heat ratio of the hot exhaust gases are matched by utilizing a cold mixture of argon and Freon-12. Solutions are obtained for a hypersonic corner flow and a supersonic rectangular flow in order to provide the upstream boundary conditions. The computational test examples also provide a comparison of this flow with that of air as the expanding supersonic jet, where the specific heats are assumed to be constant. It is shown that the three-dimensional computational fluid capabilities developed for these types of flow may be utilized to augment the conventional wind tunnel studies of scramjet afterbody flows using cold simulant exhaust gases, which in turn can help in the design of a scramjet internal-external nozzle.
    Keywords: AERODYNAMICS
    Type: International Conference on Hypersonic Aerodynamics; Sept. 4-6, 1989; Manchester
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    NASA TECHNICAL REPORTS
  • 4
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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
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4632 , A-94053 , NAS 1.15:4632 , USAATCOM-TR-94-A-011
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    2ND MANNED SPACE FLIGHT MEETING (1963)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: Collection of papers concerning u.s. manned space flight, including the mercury, gemini, and apollo projects
    Keywords: AERODYNAMICS
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  • 6
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    2nd Manned Space Flight Meeting (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Second manned space flight meeting
    Keywords: AERODYNAMICS
    Type: Manned Space Flight Meeting; Apr 22, 1963 - Apr 24, 1963; Dallas, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    2nd NASA CFD Validation Workshop (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: 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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  • 8
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    3-D axial blade row flow field inviscid finite volume prediction and verification (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A modification of the unsteady finite volume three-dimensional Euler scheme of Denton (1982) is developed to provide more accurate steady state solutions at enhanced convergence rates, and it is assessed for application to detailed axial blade row flow predictions by correlating predictions with data for a wide range of flow fields. Radial and pitchwise smoothing are minimized by the elimination of under-relaxing while time marching, by the addition of an internal transient averaging scheme, and by the use of the maximum stable local time step for each grid element. Results show that the flow field is accurately predicted in regions of primarily axial pressure gradients, though the predictions do not correlate well with the data in regions of strong nonaxial pressure gradients. Though the scheme is second order accurate in the axial direction, it is first order accurate in the other dimensions, smearing the flow field details.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0432
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    3-D composite velocity solutions for subsonic/transonic flow over afterbodies (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A composite velocity procedure for the three-dimensional reduced Navier-Stokes equations is developed. The velocity components are written as a combined multiplicative and additive composite of viscous like velocities and pseudo-potential or inviscid velocities. The solution procedure is then consistent with both asymptotic inviscid flow and boundary layer theory. For transonic flow cases, the Enquist-Osher flux biasing scheme developed for the full potential equation is used. A quasi-conservation form of the governing equations is used in the shock region to capture the correct rotational behavior. The composite velocity procedure is applied for the solution of three-dimensional afterbody problems.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-1837
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  • 10
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    3-D composite velocity solutions for subsonic/transonic flows (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A composite velocity procedure for the three-dimensional reduced Navier-Stokes equations is developed. In the spirit of matched asymptotic expansions, the velocity components are written as a combination multiplicative and additive composite of viscouslike velocities and pseudopotential or inviscid velocities. The solution procedure is then consistent with both asymptotic inviscid flow and boundary layer theory. For transonic flow cases, the Enquist-Osher flux biasing scheme developed for the full potential equation is used. A quasi-conservation form of the governing equations is used in the shock region to capture the correct rotational shock with the standard nonconservation form of the equations used in nonshock regions. The consistent coupled strongly implicit procedure coupled with a plane relaxation procedure is used to solve the discretized equations.
    Keywords: AERODYNAMICS
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