F. E. Mc Lean

Bio: F. E. Mc Lean is an academic researcher. The author has contributed to research in topics: Lift-to-drag ratio & Hypersonic speed. The author has an hindex of 1, co-authored 1 publications receiving 4 citations.

Supersonic aerodynamic characteristics of some simplified and complex aircraft configurations which employ highly swept twisted-and-cambered arrow-wing planforms

Abstract: Application of low drag-due-to-lift concept of linearized theory to the studies of twist and camber of isolated wing and wing-body configurations of supersonic aircraft

Numerical method of estimating and optimizing supersonic aerodynamic characteristics of arbitrary planform wings

Abstract: Numerical method to obtain pressure distribution on arbitrary wing planform of various surface shapes with attention to aerodynamic characteristics

Numerical method for design of minimum-drag supersonic wing camber with constraints on pitching moment and surface deformation

Abstract: A numerical method, based on linearized theory, for designing minimum-drag supersonic wing camber surfaces of arbitrary planform for a given lift, with options for constraining the pitching moment and/or the surface deformation at the trailing edge of the root chord and for selecting any desired combination of eight specified wing-loading distributions to be employed in the optimization procedure is presented. Two examples are given to illustrate applications of the method. The results indicate that relatively small drag penalties are incurred in designing wings to be self-trimming and to have a reasonable camber surface.

Effects of leading edge sweep angle and design lift coefficient on performance of a modified arrow wing at a design Mach number of 2.6

Abstract: Wing models were tested in the high-speed section of the Langley Unitary Plan wind tunnel to study the effects of the leading-edge sweep angle and the design lift coefficient on aerodynamic performance and efficiency. The models had leading-edge sweep angles of 69.44 deg, 72.65 deg, and 75.96 deg which correspond to values of the design Mach-number-sweep-angle parameter (beta cotangent A) sub DES of 0.6, 0.75, and 0.9, respectively. For each sweep angle, camber surfaces having design lift coefficients of 0,0.08, and 0.12 at a design Mach number of 2.6 were generated. The wind-tunnel tests were conducted at Mach numbers of 2.3, 2.6, and 2.96 with a stagnation temperature of 338.7 K (150 F) and a Reynolds number per meter of 9.843 times 10 to the 6th power. The results of the tests showed that only a moderate sweeping of the wing leading edge aft of the Mach line along with a small-to-moderate amount of camber and twist was needed to significantly improve the zero-lift (flat camber surface) wing performance and efficiency.

A linearized theory method of constrained optimization for supersonic cruise wing design

Abstract: A linearized theory wing design and optimization procedure which allows physical realism and practical considerations to be imposed as constraints on the optimum (least drag due to lift) solution is discussed and examples of application are presented. In addition to the usual constraints on lift and pitching moment, constraints are imposed on wing surface ordinates and wing upper surface pressure levels and gradients. The design procedure also provides the capability of including directly in the optimization process the effects of other aircraft components such as a fuselage, canards, and nacelles.