3 edition of Effect of leading-edge load constraints on the design and performance of supersonic wings found in the catalog.
Effect of leading-edge load constraints on the design and performance of supersonic wings
Christine M. Darden
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va
Written in English
|Other titles||Effect of leading edge load constraints on the design and performance of supersonic wings.|
|Statement||Christine M. Darden.|
|Series||NASA technical paper -- 2446.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.|
|The Physical Object|
The wing-design procedure presented in this report is a logical extension of the numerical method based on linear theory described in reference 3 and is intended to pro-vide a more versatile system for the design of supersonic wings. Whereas the method as applied in reference 3 determines a combination of three specified wing-loading dis-. distribution on the wing with concave leading edge, though observable, were much less. The pressure distribu- tion on the two wings has been calculated using the concept of an 'equivalent delta wing', but modified to take into account the upstream effect.
For those high wing designs that house the main gear in wing-mounted engine nacelles or in the wings themselves (Twin Commander, F/, Dash 7/8, B/32), the gear must be made much longer, and therefore, much heavier. A long main gear design is also more prone to structural failure in a hard or poorly executed crosswind landing. From Summary: "The effects of deflecting full-span, constant-chord, leading-edge flaps, having either round or sharp leading edges, upon the lift, drag, and pitching moment characteristics of a model of an interceptor-type aircraft have been determined experimentally at subsonic and supersonic speeds. Results indicate that the variations of lift with angle of attack and of pitching moment with Author: John C. Heitmeyer.
consumed considerable time and money. Also, not only does this procedure not guarantee an optimum configuration satisfying multiple design constraints, it almost precludes such a configuration because the efforts devoted to the initial steps in the design process become progressively harder to change. Emperor M Supersonic Business Jet - Preliminary Design Report 1. 1 PENGUIN AEROSPACE Emperor M Supersonic Business Jet MAE A – Preliminary Design of Aircraft Professor O.O. Bendiksen Group Members: Dylan Fagrey (Weights, CG, Layout) Lowell Mansilla (Propulsion and Performance) Cullen McAlpine (Aerodynamics) Jason Ro (Stability and Control, CG).
Record of North American geology for 1890
Peter the leader
The Freer Indian sculptures.
Chinese herb class.
In the Footsteps of Pope John Paul II
Journey to Mizar
The way of light
The Shy Little Kitten (A Billion Golden Memories of Little Golden Readers)
MASH goes to Moscow
Strongly correlated electron systems III
A physico-chemical method for the estimation of water in certain organic substances
Ground-water-quality data from the Powder River structural basin and adjacent areas, northeastern Wyoming
Get this from a library. Effect of leading-edge load constraints on the design and performance of supersonic wings. [Christine M Darden; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.].
wings indicate that aerodynamic performance bene-fits can also be obtained by employing leading-edge flaps at supersonic speeds (refs.
5 and 6). A cooperative wing design program has been es-tablished between NASA and General Dynamics. The purpose of this program is to evaluate at supersonic speeds the effect of camber as well asFile Size: 3MB.
Inspired by humpback whale's flippers [1, 2], this study investigated the effect of aspect ratio and shape of protuberances on the performance of airfoil with protuberances on leading edge. In the effort to delay flow separation and the formation of leading-edge vortices, two constrained, linear-theory optimization approaches were used to limit the loadings on the leading edge of a.
Effect of Wing Geometry on Lift at Supersonic Speeds 17 Journal of Engineering Science and Technology Special Issue 8/ Nomenclatures A Aspect ratio b Wing span, m CL Lift coefficient CLα Lift-force curve slope, 1/rad. CMAC Mean aerodynamic chord, m Cr Root chord, m Ct Tip chord, m c Speed of sound, m/s M Mach number M∞ Free stream Mach numberFile Size: 1MB.
A design study for a supersonic business jet with variable sweep wings is presented. A comparison with a fixed wing design with the same technology level shows the fundamental differences. It is concluded that a variable sweep design will show worthwhile advantages over.
The performance of these six profiles is compared with basic airfoil performance. In this paper, the effect of blending distance from leading edge of airfoil on aerodynamic performance is also determined.
Different five blending distances from leading edge are analyzed and compared with basic profile. An investigation has been made in the N.P.L. 18 in. x 14 in. Tunnel of the effects of leading- edge modifications on the flow and forces on an untapered wing of 50 deg leading-edge sweep, at stream Mach numbers between and Seven leading-edge profiles were tested, ranging from a droopedFile Size: 6MB.
Arriving at the leading edge from below the flow needs to do a U-turn around the leading edge to keep following the wing shape and flow towards the "extrados" and keep on with its life.
Therein lies the problem: when finally arriving at the leading edge, the air has non-zero speed (zero speed only occurs at stagnation point, of which there is. parameters is examined.
The aileron design (item 17) is a rich topic in wing design process and has a variety of design requirements, so it will not be discussed in this chapter. Chapter 12 is devoted to the control surfaces design and aileron design technique (as.
Topology Optimization of Adaptive Compliant Aircraft Wing Leading Edge M.J. Santer⁄ and S. Pellegrinoy University of Cambridge, Cambridge, CB2 1PZ, UK A network analysis technique is introduced which may be used for determining and parameterizing the load paths in a lattice structure to enable a load path-based topologyFile Size: 1MB.
The dynamic aeroelastic effects on wings modified with bio-inspired leading-edge (LE) tubercles are examined in this study.
We adopt a state-space aeroelastic model via the coupling of unsteady vortex-lattice method and a composite beam to evaluate stability margins as a result of LE tubercles on a generic by: 2.
THE EFFECT OF LEADING EDGE PROTUBERANCES ON THE PERFORMANCE OF SMALL ASPECT RATIO FOILS J.-H. CHEN1,c, S.-S. LI1, V.T. NGUYEN1,2. Department of Systems & Naval Mechatronic Engineering, National Cheng Kung University, Tainan,Taiwan.
Faculty of Transportation Mechanical Engineering, Da Nang University of Technology, Da Nang. The additional load caused higher bending and torsion on the wing structure, exceeding design limits.
The flight limits, in terms of angle of attack and sideslip, would have to be restricted with an attendant reduction in performance. The recovery plan resulted in modification to.
significant effect on the laminar bubble separation extent and reattachment. They also noted that separation without reattachment occurred when the ice shape was placed closer to the leading edge (xic less than 10% chord on a NACA64AOlO with WC Cited by: A discussion of the pros and cons of delta wings (see schematic in Figure ) is given in Appendix C, The delta wing, and will not be elaborated on here, other than that they are planform shapes intended for high-subsonic or supersonic aircraft and not low-subsonic though it is certainly possible to use delta wings for low-speed airplanes (as evident by the Dyke Delta) it.
The Tubercle Effect was first discovered during research conducted by Dr. Frank Fish. the vortex-dominated flow over the wings with Leading Edge scallops the maximum loss in prestall lift for the semispan The complexity of the fluid flow imposes a number of design constraints with respect to aerodynamic performance as well as.
the leading edge of a rectangular NACA aerofoil decreased its performance in the pre-stall regime. In the post-stall region, it was found that the lift coefficient of the aerofoils with protuberances on the leading edge had a higher lift coefficient and drag was independent of the geometry.
Thus. Effect of a Single Leading-edge Protuberance on NACA 63 Airfoil Performance — 3 good agreement is demonstrated while the Reynold number is a bit different.
Overall, the simulation results fit better with the experiment at higher Reynolds number Re=× . The reason may be Lascribed to the fully turbulence modelFile Size: KB.
Supersonic diffusers. See also what's at your library, or elsewhere. Broader term: Aerodynamics, Supersonic; Filed under: Supersonic diffusers Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to / (Washington: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.
Report presenting wind-tunnel testing to determine the effect of leading-edge sweepback on the lift, drag, and pitching-moment characteristics of 3-percent-thick wings of aspect ratio 3 and taper ratio Increasing the leading-edge sweepback of wings decreased both the lift-curve slope and the variation of static longitudinal stability at zero lift with Mach by: 1.regions is an essential part.-of aircraft aerodynamics.
For wings with highly swept leading edges the flow on the suction side tends to spiral in the manner of a vortex parallel to the leading edge. The presence of the rotating flow provides lift augmentation at low supersonic speeds, up to the point where the flow breaks down due to viscous File Size: 1MB.
In this paper, by means of computational fluid dynamics, a significant study has been made on the effects of geometric parameters of wing with capability of flying efficiently and cost-effectively at supersonic condition.
Multi-objective optimization has been performed for the aerodynamic shape optimization of the wing configuration. The three-dimensional wing shape defined by four Cited by: 2.