3 edition of Conical Euler solution for a highly-swept delta wing undergoing wing-rock motion found in the catalog.
Conical Euler solution for a highly-swept delta wing undergoing wing-rock motion
Elizabeth M. Lee
by National Aeronautics and Space Administration, Langley Research Center in Hampton, Va
Written in English
|Statement||Elizabeth M. Lee and John T. Batina.|
|Series||NASA technical memorandum -- 102609.|
|Contributions||Batina, John T., Langley Research Center.|
|The Physical Object|
A delta wing has the advantage of a large sweep angle but also greater wing area than a simple swept wing to compensate for the loss of lift usually experienced in sweepback. But, at still higher supersonic Mach numbers, the Mach cone may approach the leading edge of even a highly swept delta wing. Close Drawer Menu Open Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of .
A series of calculations for a wing-body combination with delta wings at Mach numbers of 3, 4, and 5 and angles of attack up to 25 deg was made to demonstrate the feasibility of the use of the Euler equations to handle separated rotational flows. Some comparisons with experimental pressure distributions and fin load were made with good agreement. the vortex flow characteristics of a highly swept delta wing ( sweep) undergoing both steady and unsteady pitching motions. The effects of several parameters were examined, including motion amplitude, pitching frequency, Reynolds number, and leading edge geometry.
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Get this from a library. Conical Euler solution for a highly-swept delta wing undergoing wing-rock motion. [Elizabeth M Lee; John T Batina; Langley Research Center.].
CONICAL EULER SOLUTION FOR A HIGHLY-SWEPT DELTA WING UNDERGOING WING-ROCK MOTION Elizabeth M. Lee John T.
Batina NASA Langley Research Center Hampton, Virginia Summarv Modifications to an unsteady conical Euler code for the free-to-roll analysis of highly- swept delta wings are described.
Conical Euler solution for a highly-swept delta wing undergoing wing-rock motion Modifications to an unsteady conical Euler code for the free-to-roll analysis of highly-swept delta wings are. A conical Euler code was developed to study unsteady vortex-dominated flows about rolling highly-swept delta wings, undergoing either forced or free-to-roll motions including active roll suppression.
A conical Euler methodology was developed to study unsteady vortex-dominated flows about rolling highly swept delta wings undergoing either forced or free-to-roll motions.
Here u and u * are the axial disturbance velocities of the thin and thick-symmetrical delta wing components of the wedged delta wing. The wedged delta wing has sonic leading edges (LEs) for ν = 1, i.e. for the value of the Mach number M ∞ ≅ For M ∞ delta wing has subsonic LEs and for M ∞ > (ν > 1) it has supersonic LEs.
A solution for a delta wing is obtained in a simplified formulation of the optimization problem and a theoretical analysis. It is shown that the optimal conical wing is formed by elements of elliptical cones and planes.
Numerical modelling of the flow of a non-viscous non-heat-conducting gas past the wing is performed, and the results of the. swep. flat phite delta wing computed using the conical Euler equations at vortex-dominated flows about highly-swept delta wings, t4 This.
The wing-rock time history from Ref. J. Elzebda, A. Nayfeh and D. Mook, "Development of an analytical model of wing rock for slender delta wings," Journal of Aircr (). Lee and J. Batina, "'Conical Euler solution for a highly-swept delta wing undergoing wing-rock motion," NASA TMNew York: Franklin Watts ().
Jun, Y. and Nelson R. “Leading Edge Vortex Dynamics on a Delta Wing Undergoing a Wing Rock Motion,” AIAA Paper (). Kandil, O. and Salman A. ’’Three-Dimensional Simulation of Slender Delta Wing Rock and Divergence,” AIAA Paper ().
A conical Euler code was developed to study unsteady vortex-dominated flows about rolling, highly swept delta wings undergoing either forced motions or free-to-roll motions that include active. This banner text can have markup. web; books; video; audio; software; images; Toggle navigation.
In the case of lifting wings, the solution can be constructed as an improving shape variation to the flat delta wing. 2 Problem Statement Consider a delta wing at supersonic flow (figure 1). It is required to minimize the aerodynamic drag and to determine the corresponding wing warping for given lift.
The. Newsome, R. Euler and Navier-Stokes solutions for flow over a conical delta wing. AIAA J. 24, – Phillips, O.
The intensity of aeolian tones. The second type of undesirable rotary motion is the tumbling, illustrated in Fig. In this case, the longitudinal moment of inertia I xx is larger than the spanwise one I yy and the wing stall may initiate autorotation about the y axis.
This phenomenon was well documented after World War II by Stone and Bryant who explored flying-wing concepts, but the airplanes of that era had considerably. A delta wing is a wing shaped in the form of a triangle.
It is named for its similarity in shape to the Greek uppercase letter delta (Δ). Although long studied, it did not find significant applications until the jet age, when it proved suitable for high-speed subsonic and supersonic the other end of the speed scale, the Rogallo flexible wing proved a practical design for the hang.
Steady, inviscid, supersonic flow past conical wings is studied within the context of irrotational, nonlinear theory. An efficient numerical method is developed to calculate cones of arbitrary section at incidence.
The method is fully conservative and implements a body conforming mesh generator. The conical potential is assumed to have its best linear variation inside each cell; a secondary.
Highly swept wings tend to produce the stable separated conical vortex type flow described in Chapter 1, at relatively low angles of attack. For aircraft Fig. Broad delta wing The Vulcan bomber originally had a simple triangular delta wing.
This was later modified by the addition of a leading edge extension which. In this context unsteady Euler calculations are performed for a delta wing with 53° leading-edge sweep in the transonic and supersonic region for different angles of attack.
The wing is fitted with two trailing-edge flaps, an inboard and an outboard flap. The main features of the Euler code and grid generator used are described.
The story of development of the swept wing and the delta wing is long and fascinating. Bear with me while I try to complete it in two parts. The swept wing came first. It enabled aircraft to fly near the speed of sound - “transonic speed” - and is.
The delta wing model layout is illustrated in Fig. the figure shows, it is a half-wing which has leading-edge sweep angle of 60°. The upper surface is flat and the leading edge is sharp (15° angle made by the lower and upper surfaces at the leading edge) to minimize the effects of airfoil and leading edge shapes on the flow field.The big differences between a delta wing and a straight wing break down into thinking about them in two ways: aspect ratio and sweep.
A delta wing is going to have a small aspect ratio (short and stubby) as well as sweep. Straight wings can have a small aspect ratio (think F) or large aspect ratio (more like a .and ively controlled the wing rock response of an 80 ° swept delta wing at 30 ° angle of attack and Mach num-ber of by using tuned antisymmetric leading-edge flap oscil-lations.
They later applied the locally conical Euler equations-to the same problem at Math The three-dimensional flow.