Computational Test Cases for a Clipped Delta Wing with Pitching and Trailing-Edge Control Surface Oscillations PDF Download
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Author: Robert M. Bennett
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 96
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Author: Robert M. Bennett
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 96
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720449645
Category :
Languages : en
Pages : 90
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Book Description
Computational test cases have been selected from the data set for a clipped delta wing with a six-percent-thick circular-arc airfoil section that was tested in the NASA Langley Transonic Dynamics Tunnel. The test cases include parametric variation of static angle of attack, pitching oscillation frequency, trailing-edge control surface oscillation frequency, and Mach numbers from subsonic to low supersonic values. Tables and plots of the measured pressures are presented for each case. This report provides an early release of test cases that have been proposed for a document that supplements the cases presented in AGARD Report 702.Bennett, Robert M. and Walker, Charlotte E.Langley Research CenterCOMPUTATIONAL FLUID DYNAMICS; DELTA WINGS; AIRFOIL PROFILES; CONTROL SURFACES; PITCH (INCLINATION); WIND TUNNEL TESTS; UNSTEADY AERODYNAMICS; TRANSONIC FLOW; COMPUTERIZED SIMULATION; ANGLE OF ATTACK; TRAILING EDGES; MACH NUMBER; WIND TUNNEL MODELS; ATTITUDE CONTROL; OSCILLATIONS
Author: Robet M. Bennett
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
Steady and unsteady measured pressures for a Clipped Delta Wing (CDW) undergoing pitching oscillations and trailing-edge control surface oscillations have been presented in Ref I and 2. From the several hundred compiled data points, 22 static cases, 12 pitching-oscillation cases, and 12 control-surface-oscillation cases have been proposed for Computational Test Cases to illustrate the trends with Mach number, reduced frequency, and angle of attack. The planform for this wing was derived by simplifying the planform of a proposed design for a supersonic transport which is described (Ref 3) as the Boeing 2707-300. The strake was deleted. the resulting planform was approximated by a trapezoid with an unswept trailing edge, and the twist and camber were removed. In order to facilitate pressure instrumentation, the thickness was increased to 6 percent from the typical 2.1 to 3 percent for the supersonic transport. The airfoil is thus a symmetrical circular arc Section with tie 0.06 of similar planform but with a thinner airfoil of tic 0.03 was used in the flutter investigations of Ref 4 and 5, and the buffet and stall flutter investigation of Ref 6. Flutter results are also reported both for the 3 per event thick simplified wing and for a more complex SST model in Ref 7.
Author:
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1020
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Author: Hans Josef Rath
Publisher: Springer Science & Business Media
ISBN: 3540332871
Category : Technology & Engineering
Languages : en
Pages : 543
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Book Description
This volume collects contributions to the 14th Symposium of the STAB (German Aerospace Aerodynamics Association). The association involves German scientists and engineers from universities, research establishments and industry who are doing research and project work in numerical and experimental fluid mechanics and aerodynamics, mainly for aerospace but for other applications, too. The volume gives a broad overview of ongoing work in Germany in this field.
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 182
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Author: Werner Haase
Publisher: Springer Science & Business Media
ISBN: 3540454896
Category : Technology & Engineering
Languages : en
Pages : 381
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Book Description
Aircraft design processes require extensive work in the area of both aerodynamics and structure, fonning an environment for aeroelasticity investigations. Present and future designs of European aircraft are characterized by an ever increasing aircraft size and perfonnance. Strong weight saving requirements are met by introduction of new materials, leading to more flexible structure of the aircraft. Consequently, aeroelastic phenomena such as vortex-induced aeroelastic oscillations and moving shock waves can be predominant and may have a significant effect on the aircraft perfonnance. Hence, the ability to estimate reliable margins for aeroelastic instabilities (flutter) or dynamic loads (buffeting) is a major concern to the aircraft designer. As modern aircrafts have wing bending modes with frequencies that are low enough to influence the flight control system, demands on unsteady aerodynamics and structural analysis to predict flight control effectiveness and riding comfort for passengers are extremely high. Therefore, the aircraft industries need an improved capacity of robust, accurate and reliable prediction methods in the coupled aeroelastic, flight mechanics and loads disciplines. In particular, it is necessary to develop/improve and calibrate the numerical tools in order to predict with high level of accuracy and capability complex and non-classical aeroelastic phenomena, including aerodynamic non-linearities, such as shock waves and separation, as well as structural non-linearities, e. g. control surface free-play. Nowadays, robust methods for structural analysis and linearised unsteady aerodynamics are coupled and used by the aircraft industry to computationally clear a new design from flutter.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1154
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
