Author: T. M. PrituloPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Favorable Interference of Optimized Wing-body Combination with Inlets at Supersonic Speed
Author: T. M. PrituloWind-tunnel Investigation of Favorable Interference to Increase Lift-drag Ratios of Supersonic Aircraft: Part Ii: an Optimized Wing-body-inlet Configuration
Author: Richard M. HARTLEYPublisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
The results of wind-tunnel tests conducted at a Mach number of 2.87 to investigate favorable interference effects on wing-body-inlet configurations are presented. The engine air inlet location and the body indentation angle for maximum lift increments were determined. These favorable lift increments correspond to about 20 percent of the cruise lift required for an attack aircraft. A fence, attached to the wing to reflect the shock wave emanating from the engine air inlet and to intensify the pressure field, increased the inboard lift but not sufficiently to overcome the resulting loss in lift ffrom the outboard section of the wing. (Author).
Favorable Wing-body Interference for Aircraft at Supersonic Speed: an Analytic Study of Design Parameters
Author: R. C. MEYER1st AIAA Aircraft Engineering, Technology, and Operations Congress
Author: 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
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 : 24
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.
Scientific and Technical Aerospace Reports
Author: Summary Description of a Method of Optimizing Camber Surfaces for Wing-body Combinations at Supersonic Speeds
Author: Wing-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.
Author: Jack N. Nielsen