Author: Odell A. MorrisPublisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Aerodynamic Characteristics in Pitch of Several M-wing-body Combinations at Mach Numbers of 2.40, 2.60, and 2.86
Author: Odell A. MorrisAerodynamic Characteristics in Pitch of Several M-wing-body Combinations at Mach Numbers of 2.40, 2.60, and 2.86
Author: Odell A. MorrisPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42
Book Description
Aerodynamic Characteristics in Pitch of Several Ring-wing-body Configurations at a Mach Number of 2.2
Author: Odell A. MorrisPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 26
Book Description
Aerodynamic Characteristics of Several Cranked Leading-edge Wing-body Combinations at Mach Numbers from 0.4 to 2.94
Author: Edward J. HopkinsPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 98
Book Description
Aerodynamic Characteristics in Pitch at a Mach Number of 2.01 of Several Wing-body Combinations with Wedge-shaped Bodies Located Above and Below a 54.5 ̊swept Delta Wing
Author: Odell A. MorrisPublisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 32
Book Description
Aerodynamic Characteristics in Pitch at a Mach Number of 2.01 of Several Wing-body Combinations with Wedge-shaped Bodies Located Above and Below a 54.5 Degree Swept Delta Wing
Author: Odell A. MorrisAerodynamic Characteristics in Pitch of Several Ring-wing-body Configurations at a Mach Number of 2.2
Author: Odell MorrisPublisher:
ISBN:
Category :
Languages : en
Pages : 26
Book Description
An investigation was conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.2 to determine the aerodynamic characteristics of several ring-wing--body configurations. This investigation included tests for the bodies alone and for the ring-wing--body combinations; these tests were conducted through an angle-of-attack range from about -4 to 11 degrees. The data indicated that sizable reductions in body wave drag were obtained for the concaveafterbody configuration as a result of the favorable interference produced by the ring wing. However, a large percentage of the total drag was produced by the ring wing and struts, and thus the ring-wing configurations of these tests appear to offer no drag advantage over a conventional wing-body configuration. Of the three configurations tested, the half-ring wing in combination with a body having a parabolic afterbody had the lowest drag (0.35) and the highest maximum liftdrag ratio (4.9).
Longitudinal Aerodynamic Characteristics at Mach Number 2.02 of a Series of Wing-body Configurations Employing a Cambered and Twisted Arrow Wing
Author: Harry W. CarlsonEffects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87
Author: Royce L. McKinneyPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations
Author: Harry W. CarlsonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.