Author: Dennis E. FullerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63
Author: Dennis E. FullerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Effect of Cross-section Shape on the Aerodynamic Characteristics of Bodies at Mach Numbers from 2.50 to 4.63
Author: Dennis E. FullerEffect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63
Author: Dennis E. FullerEffects of Body Shape on the Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6
Author: Walter P. NelmsPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 68
Book Description
Longitudinal Aerodynamic Characteristics of Several High-drag Bodies at Mach Numbers from 1.50 to 4.63
Author: James F. CampbellPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Aerodynamic Characteristics, Including Effect of Body Shape, of a Mach 6 Aircraft Concept
Author: Gregory D. RiebePublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 34
Book Description
Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0
Author: Leland Howard JorgensenPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 88
Book Description
An experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a,b axis system was rotated 900, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.
Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0
Author: Leland Howard JorgensenPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132
Book Description
Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86
Author: Dennis E. FullerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Transonic Aerodynamic Characteristics of Several Bodies Having Elliptical Cross Sections and Various Plan Forms
Author: Robert A. TaylorPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Book Description