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J. E. Lamar

Bio: J. E. Lamar is an academic researcher from Langley Research Center. The author has contributed to research in topics: Aircraft flight mechanics & Aerodynamics. The author has an hindex of 1, co-authored 1 publications receiving 2 citations.

Papers
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Proceedings ArticleDOI
01 Aug 1982
TL;DR: In this paper, the NASA Vortex Lattice and Modified Multhopp methods are applied to aircraft design problems at high subsonic speeds, and the suction analogy is used to provide estimates associated with vortex-flow aerodynamics.
Abstract: This paper deals with selected linearized-aerodynamic and vortex-flow methods as applied to aircraft design problems at high subsonic speeds. In particular, the NASA Vortex Lattice and Modified Multhopp methods are the linearized techniques employed, and the suction analogy is used to provide estimates associated with vortex-flow aerodynamics. Many examples are given as to how researchers at Langley have used these methods to design the high subsonic, wing-mean-camber shapes for various configurations such as a supersonic transport, high-aspect-ratio transport, trapezoidal fighter wing, strake wing, tandem wing, joined wing, delta wing, and slender cranked wing. Many of these have been built, tested, and have had their data compared with theory. In addition, a technique for defining efficiently performing strake planforms for use in strake-wing combinations is discussed, and further improvements in wing design are outlined. The latter may be obtained by using higher-ordered linear panel methods as well as nonlinear-transonic methods.

3 citations


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Book ChapterDOI
24 Jul 2019
TL;DR: The conceptual design parameters and design processes which are used to access the development of the generic stability and control method are identified and discussed in Sect.
Abstract: The conceptual design parameters and design processes which are used to access the development of the generic stability and control method are identified and discussed in Sect. 4.4. Primarily, design related commonalties and peculiarities for the range of conventional and unconventional aircraft types are considered.

1 citations

Proceedings ArticleDOI
01 Jan 1984
TL;DR: In this paper, an aerodynamic model applicable to describe the nonlinear aerodynamic reactions to a delta wing maneuvering at high angles of attack is investigated, and time-histories of the aerodynamic responses to complex motions are generated by means of the model and the evaluated aerodynamic data.
Abstract: The regime of validity of an aerodynamic mathematical model, applicable to describe the nonlinear aerodynamic reactions to a delta wing maneuvering at high angles of attack is investigated. An unsteady vortex-lattice method is used to compute the unsteady flowfields, and thus to evaluate the aerodynamic data required by the model, in terms of specified characteristic motions. Time-histories of the aerodynamic responses to complex motions are generated by means of the model and the evaluated aerodynamic data, and are compared with baseline aerodynamic responses obtained from direct vortex-lattice computations. The validity of the mathematical modeling approach for the maneuvering delta wing is demonstrated by the close agreement of the force and moment responses obtained from the two approaches.

1 citations

Journal ArticleDOI
TL;DR: A review of the use of the vortex lattice method (VLM) in modeling the general aerodynamics of subsonic and supersonic aircraft can be found in this article .
Abstract: There has been a renewed interest in developing environmentally friendly, economically viable, and technologically feasible supersonic transport aircraft and reduced order modeling methods can play an important contribution in accelerating the design process of these future aircraft. This paper reviews the use of the vortex lattice method (VLM) in modeling the general aerodynamics of subsonic and supersonic aircraft. The historical overview of the vortex lattice method is reviewed which indicates the use of this method for over a century for development and advancements in the aerodynamic analysis of subsonic and supersonic aircraft. The preference of VLM over other potential flow-solvers is because of its low order highly efficient computational analysis which is quick and efficient. Developments in VLM covering steady, unsteady state, linear and non-linear aerodynamic characteristics for different wing planform for the purpose of several different types of design optimisation is reviewed. For over a decade classical vortex lattice method has been used for multi-objective optimisation studies for commercial aircraft and unmanned aerial vehicle’s aerodynamic performance optimisation. VLM was one of the major potential flow solvers for studying the aerodynamic and aeroelastic characteristics of many wings and aircraft for NASA’s supersonic transport mission (SST). VLM is a preferred means for solving large numbers of computational design parameters in less time, more efficiently, and cheaper when compared to conventional CFD analysis which lends itself more to detailed study and solving the more challenging configuration and aerodynamic features of civil supersonic transport.