Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities PDF Download
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Author: Clarence John Schueler
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 242
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Book Description
Some of the techniques in current use for measuring dynamic stability derivatives in wind tunnels are described, with emphasis given to the important features of balance system design, data reduction methods, instrumentation and typical balance systems. The use of gas bearings for dynamic stability and roll damping balances is treated and a three-degree-of-freedom balance system employing a spherical gas bearing is described. (Author).
Author: Clarence John Schueler
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 242
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Book Description
Some of the techniques in current use for measuring dynamic stability derivatives in wind tunnels are described, with emphasis given to the important features of balance system design, data reduction methods, instrumentation and typical balance systems. The use of gas bearings for dynamic stability and roll damping balances is treated and a three-degree-of-freedom balance system employing a spherical gas bearing is described. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 700
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Bandu N. Pamadi
Publisher: AIAA
ISBN: 9781600860997
Category : Aerodynamics
Languages : en
Pages : 810
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
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Book Description
Author: Frederick B. Cyran
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
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Book Description
Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.
Author: Frederick B. Cyran
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 92
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Book Description
Wind tunnel sting support interference effects on dynamic stability derivatives, static pitching moment and base pressure of a blunt, 7-deg cone were investigated at subsonic and transonic Mach numbers. The cone was tested with sting configurations having a variable effective sting length ranging from 1 to 3.3 model base diameters, at angles of attack ranging from 0 to 30 deg. A forced-oscillation system was utilized to obtain data at a frequency of oscillation of approximately 5.3 Hz, and at an amplitude of 1 deg. The Reynolds number, based on model base diameter, was nominally 1.8 million, which produced a turbulent boundary layer over the aft portion of the model. The nature of the causes of these interference effects is discussed and analyzed with respect to sting length, type of measurement, and Mach number, with emphasis on defining critical sting length and on predicting minimal interference sting configurations for dynamic stability testing. The results showed that the critical sting length depended on the type of measurement used as the interference indicator, Mach number, and angle of attack. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting diameter-to-model base diameter (0.22) investigated. (Author).
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 372
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Book Description
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 142
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category :
Languages : en
Pages : 558
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 310
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Book Description
