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  • 1
    Electronic Resource
    Electronic Resource
    Piezo-electric foils as a means of sensing unsteady surface forces (1989)
    Springer
    Experiments in fluids 7 (1989), S. 111-118 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract The experimental determination of steady and unsteady surface forces is an elementary problem in experimental fluid dynamics, e.g., in experimental aerodynamics. Up to now, unsteady forces such as pressure or shear fluctuations have been detected by means of special plug-in probes (e.g., miniature pressure transducers). An alternative and attractive technique of monitoring unsteady surface forces has become possible through the development of piezoelectric foils. With this novel type of sensor, which simply can be glued onto a surface, the piezoelectric effect of polarized plastic foils is used to register time-dependent pressure or shear loads. First of all, the paper concentrates on the fundamentals of this new measuring technique. Furthermore, some practical applications in experimental aerodynamics are outlined.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00207303
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Variable wing camber for transport aircraft (1988)
    Elsevier
    Details
    Publication Date: 1988-01-01
    Print ISSN: 0376-0421
    Electronic ISSN: 1873-1724
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Piezo-electric foils as a means of sensing unsteady surface forces (1989)
    Springer
    Details
    Publication Date: 1989-11-01
    Print ISSN: 0723-4864
    Electronic ISSN: 1432-1114
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 4
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    Types of leeside flow over delta wings (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: It is noted that so far most systematic investigations on the lee side flow over delta wings at supersonic speeds are concerned with flat upper surfaces. On the basis of these results, the paper makes an attempt to characterize the different types of flow over a wing with a delta-shaped upper surface by varying a number of parameters. It is concluded that the work should be considered a first step toward systematizing the flow over delta-shaped lee sides as well.
    Keywords: AERODYNAMICS
    Type: Zeitschrift fuer Flugwissenschaften und Weltraumforschung; 4; Mar
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Reynolds number influence on leeside flowfields (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Experimental results on the Reynolds number influence on the leeside flowfield of planar delta wings at supersonic speeds are presented. Wind tunnel experiments on two delta wing models with straight and sharp leading edges at freestream Mach number of 2.5 and 3.5 and angle of attack between 1 deg and 12.5 deg were carried out. The cross-sectional shape was triangular and the relative height was 0.25. The flow types investigated were to the left and right of the Stanbrook-Squire boundary. Under leading-edge separation conditions, the vortex position and intensity, and thus the suction pressure, vary with Re while the flow type remains nearly unchanged. In the region of separation with embedded shock, Re affects not only the shape of the separation bubble and pressure level near the leading edge but also the type of flow. At sufficiently high Re the flow type of separation with shock changes to one with shock-induced separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 16; Dec. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental study of supersonic viscous leeside flow over a slender delta wing (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to study in detail the vortical flow over the leeward side of a 70 deg swept delta wing having subsonic and supersonic leading edges. Two types of flow were encountered and studied, namely leading edge separation and separation with a shock. Especially for the latter type, Reynolds number plays an important role and unexpected strong streamwise vortices were observed. An optical method is described to obtain a first aproximation of shear stress values in the streamwise direction across the wing span.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-81248 , A-8408
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Leeward flow over delta wings at supersonic speeds (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A survey was made of the parameters affecting the development of the leeward symmetric separated flow over slender delta wings immersed in a supersonic stream. The parameters included Mach number, Reynolds number, angle of attack, leading-edge sweep angle, and body cross-sectional shape, such that subsonic and supersonic leading-edge flows are encountered. It was seen that the boundaries between the various flow regimes existing about the leeward surface may conveniently be represented on a diagram with the components of angle of attack and Mach number normal to the leading edge as governing parameters.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81187 , A-8117
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Measurement and visualization of skin friction on the leeside of delta wings in supersonic flow (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The reported investigation was conducted with the aid of the NASA Ames High Reynolds Number Wind Tunnel. The flow conditions considered involved free stream Mach numbers of 2 and 3, and a Reynolds number of approximately 10,000,000 p. m. The employed model was a delta wing with an angle of 70 deg. A method reported by Tanner (1977) was used for the measurement of the skin friction. This method involves the use of a laser interferometer to determine the change in the thickness of an oil film. The procedure can also be employed for a visualization of skin friction in the form of interferograms. The investigation shows that skin friction measurements can provide a significant contribution to a physical understanding of the flow processes at the delta wing.
    Keywords: AERODYNAMICS
    Type: Symposium on Flows with Separation; Nov 23, 1981 - Nov 25, 1981; Stuttgart
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Application of a Laser Interferometer Skin-Friction Meter in Complex Flows (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A nonintrusive skin-friction meter has been found useful for a variety of complex wind-tunnel flows. This meter measures skin friction with a remotely located laser interferometer that monitors the thickness change of a thin oil film. Its accuracy has been proven in a low-speed flat-plate flow. The wind-tunnel flows described here include sub-sonic separated and reattached flow over a rearward-facing step, supersonic flow over a flat plate at high Reynolds numbers, and supersonic three - dimensional vortical flow over the lee of a delta wing at angle of attack. The data-reduction analysis was extended to apply to three-dimensional flows with unknown flow direction, large pressure and shear gradients, and large oil viscosity changes with time. The skin friction measurements were verified, where possible, with results from more conventional techniques and also from theoretical computations.
    Keywords: Lasers and Masers
    Type: NASA/TM-81-207537 , NAS 1.15:207537 , IEEE-Publ-81CH1712-9 , ICIASF 1981; 232-243|International Congress on Instrumentation in Aerospace Simulation Facilities; Sep 30, 1981; Dayton, OH; United States
    Format: application/pdf
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  • 10
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    Lee side flow for slender delta wings of finite thickness (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An experimental and theoretical investigation carried out to determine the lee side flow field over delta wings at supersonic speeds is presented. A theoretical method to described the flow field is described, where boundary conditions as a result of the experimental study are needed. The computed flow field with shock induced separation is satisfactory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75753 , ILR-23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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