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  • 1
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    A new two-dimensional oscillating wing apparatus for unsteady aerodynamics research (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An apparatus for experimental research into unsteady transonic flows is described. The apparatus, as installed in the NASA-Ames 11 by 11 Foot Transonic Wind Tunnel, can impart full two-degree-of-freedom motions at reduced frequencies to 0.3, oscillatory amplitudes to tn-2 degs, mean angles to 12 degs, Mach numbers to 1.4 and Reynolds numbers to 12x10. The test wing is fully instrumented for dynamic waveform measurements and the data can be acquired, processed, and displayed in real-time with a new computational data acquisition system. Following a description of the apparatus, sample data from a recently completed test program is presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 671-688
    Format: text
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  • 2
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    Adaptive-wall wind-tunnel development for transonic testing (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Experimental techniques for rapid assessment and correction of wall interference in an adaptive-wall wind tunnel are described. The experimental arrangement allows laser velocimetry measurements on two control surfaces and incorporates a dedicated computer for data processing. The apparatus and its instrumentation are described, and typical results from an experiment on a nonlifting NACA 0012 airfoil at M = 0.78 are discussed. It is concluded that the time to acquire laser Doppler velocimeter data should be decreased, and the possibility of using one-step algorithms should be investigated.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Journal of Aircraft; 18; Apr. 198
    Format: text
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  • 3
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    A compatibility assessment method for adaptive-wall wind tunnels (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A new method is described for assessing the compatibility between inner and outer flow regimes in adaptive-wall wind tunnels. The method is applicable to both two- and three-dimensional flows, and unlike other schemes, requires the measurement of only one velocity component. Moreover, a complete solution to the outer flowfield is not required with the new method. Computer simulations of two- and three-dimensional flows are presented along with data from a two-dimensional pilot wind tunnel test using the new method.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal; 19; Sept
    Format: text
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  • 4
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    Applications of adaptive-wall wind tunnels (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A novel processing technique for the flowfield data generated by an adaptive wall wind tunnel is presented whose basic premise is the possible undesirability of forcing such a wind tunnel to simulate free-air conditions. The concept of a 'phantom' wind tunnel is introduced for both two- and three-dimensional wind tunnels, yielding a continuous spectrum of flow fields, ranging from the original passive and ventilated configuration to a fully adaptive one. In order to implement these procedures, active control is limited to floor and ceiling surfaces.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 158-160
    Format: text
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  • 5
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    The evolution of adaptive-wall wind tunnels (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Since its inception, adaptive wall wind tunnel design has developed three major configurational possibilities: streamlined walls, variable porosity walls, and segmented plenum arrangements. All of these methods have demonstrated their feasibility for transonic flow research; development programs are noted to be underway for three-dimensional adaptive wall tunnels. With the availability of advanced computational procedures, routine angle-of-incidence or Mach sweeps may be treated numerically, while adaptive wall wind tunnels are employed for complementary point-design and for testing at flow conditions that are beyond the capabilities of current numerical modeling.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Format: text
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  • 6
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    Generalized adaptive-wall wind tunnels (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Adaptive-wall technology is being seriously considered for many aeronautical wind tunnel applications. A new degree of freedom is introduced into adaptive-wall wind tunnels. It is shown that the adaptive control system used to adjust wall boundary conditions may be used to select a wide variety of flow fields. These flow fields, in turn, maybe directly related to many useful unconfined or semiconfined flows. The generalized adaptive-wall concept is demonstrated for both two- and three-dimensional flows using simple analytical techniques.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 85-0225
    Format: text
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  • 7
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    Computer/experiment integration for unsteady aerodynamic research (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The use of a minicomputer for the acquisition and analysis of unsteady aerodynamic data is described. Some of the novel features of the system include: on-line digitization, a signal-averaging algorithm, Fourier decomposition, graphical display, and on-line theoretical computations to compare with the ongoing experiment. The system's capabilities are described using some data from a recently completed oscillating airfoil experiment.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: ICIASF ''79; International Congress on Instrumentation in Aerospace Simulation Facilities; Sep 24, 1979 - Sep 26, 1979; Monterey, CA
    Format: text
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  • 8
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    Measurements of discrete vortex noise in a closed-throat wind tunnel (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Measurements are presented of the discrete vortex noise emitted by a thin airfoil. These measurements were made in a new wind tunnel designed specifically for aerodynamic noise measurements. The tunnel is an indraft type with a 25- by 35- by 100-cm testing section and a sonic-throat noise suppressor just downstream of the test section. Directivity and standing wave patterns are presented and compared with theoretical predictions. Frequency scaling criteria are developed and compared with other investigations.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 75-488 , American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference; Mar 24, 1975 - Mar 26, 1975; Hampton, VA
    Format: text
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