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Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Author : John R. Spreiter

Publisher :

Page : 646 pages

File Size : 46,85 MB

Release : 1949

Category : Aerodynamic load

ISBN :

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Book Description

The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.







Transonic Aerodynamic Characteristics of a Wingbody Combination Having a 52.5 Degree Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of 1.1416

Author : WILLIAM B. IGOE

Publisher :

Page : 1 pages

File Size : 31,4 MB

Release : 1961

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ISBN :

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Book Description

An investigation was made of the effects of conical wing camber and supersonic body indentation on the aerodynamic characteristics of a wing-body configuration at transonic speeds. Wing aspect ratio was 3.0, taper ratio was 0.1, and quarterchord line sweepback was 52.5 with airfoil sections of 0.03 thickness ratio. The tests were conducted in the Langley 16-foot transonic tunnel at various Mach numbers from 0.80 to 1.05 at angles of attack from -4 to 14. The camberedwing configuration achieved higher lift-drag ratios than a similar plane-wing configuration. The camber also reduced the effects of wing-tip flow separation on the aerodynamic characteristics. In general, no stability or trim changes below wing-tip flow separation resulted from the use of camber. The use of supersonic body indentation improved the lift-drag ratios at Mach numbers from 0.96 to 1.05. (Author).