Author: J. G. JonesPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Interference Between Antisymmetric Body Shaping and Subsonic Leading Edges on Wing-body Combinations at Supersonic Speeds
Author: J. G. JonesWing-body Interference at Supersonic Speeds with an Application to Combinations with Rectangular Wings
Author: Jack N. NielsenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 63
Book Description
An exact theoretical method is developed that permits the determination of the pressure field of a wing-body combination having a circular body and wings with supersonic leading and trailing edges. Detailed calculations are performed for the case of a rectangular wing or all-movable control surface on a body at zero angle of attack. Design charts are presented showing the effect of interference on the lift and center-of-pressure position of the wings. The physical basis of the interference is discussed.
An Integrated Approach to the Analysis and Design of Wings and Wing-body Combinations in Supersonic Flow
Author: Ralph L. CarmichaelPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2
Author: Ross B. RobinsonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Basic Studies of Wing-Body Interference at High Angles of Attack and Supersonic Speeds
Author: Goetz H. KlopferPublisher:
ISBN:
Category :
Languages : en
Pages : 87
Book Description
The problem of computing the steady inviscid supersonic flows about thin wings having sharp subsonic leading edges and leading-edge separation is solved in this paper. Both wings alone or wings in the presence of the body are considered. To obtain an efficient procedure the steady Euler equations are used as the basic governing equations as opposed to the more complicated Navier-Stokes equation. The viscous effects, important near the sharp leading edges, are simulated by a Kutta condition applied at the leading edges of the wings. The rest of the flow field is essentially controlled by the inviscid equations. The equations, written in conservation form in generalized curvilinear coordinates, are approximated by MacCormack's second-order accurate predictor-corrector algorithm. The flow tangency conditions at the body surface are satisfied by Abbett's scheme and the outer bow-shock position by the Rankine-Hugoniot jump relations. Internal shock waves or tangentially discontinuities are captured. The slip surface emanating from the leading edge of the sharp wing excited nonlinear instabilities in the MacCormack's scheme, which were stabilized by special flow dependent fourth-order damping terms.
Mutual Interference Between a Lifting Surface and a Body of Revolution
Author: Hiroshi HoshizakiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70
Book Description
The Proper Combination of Lift Loadings for Least Drag on a Supersonic Wing
Author: Frederick C. GrantPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
Book Description
The best combination of four loadings on a delta wing with subsonic leading edges is calculated for several Mach numbers as a numerical example. The loadings considered have finite pressures everywhere on the plan form. At each Mach number the optimum combination of the four non-singular loadings has about the same drag coefficient as a flat plate with leading-edge thrust.
Selected Technical Reports
Author: United States. Federal Aviation AdministrationPublisher:
ISBN:
Category :
Languages : en
Pages : 590
Book Description
Theoretical Lift and Damping in Roll of Thin Sweptback Wings of Arbitrary Taper and Sweep at Supersonic Speeds
Author: Frank S. MalvestutoPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
Book Description
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.
A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios
Author: Richard T. WhitcombPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.