Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
An Investigation at Mach Numbers from 1.47 to 2.87 of Static Stability Characteristics of Nine Nose Cones Designed for Supersonic Impact Velocities
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 34
Book Description
Damping in Pitch and Static Stability of Supersonic Impact Nose Cones, Short Blunt Subsonic Impact Nose Cones, and Manned Reentry Capsules at Mach Numbers from 1.93 to 3.05
Author: Herman S. FletcherPublisher:
ISBN:
Category :
Languages : en
Pages : 60
Book Description
Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
An Investigation at Mach Numbers from 0.20 to 4.63 of the Aerodynamic Performance, Static Stability, and Trimming Characteristics of a Canard Configuration Designed for Efficient Supersonic Cruise Flight
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 88
Book Description
Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85
Author: Lucille C. ColtranePublisher:
ISBN:
Category : Aircraft
Languages : en
Pages : 32
Book Description
Aerodynamic Characteristics of Towed Cones Used as Decelerators at Mach Numbers from 1.57 to 4.65
Author: Nickolai CharczenkoPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 30
Book Description
Towed and sting-supported cones were tested in the wake of various payloads at supersonic speeds to determine their drag and stability characteristics. The investigation extended over a Mach number range from 1.57 to 4.65 and included such variables as Reynolds number, cone angle, ratio of cone base diameter to payload base diameter, and trailing distance. Cones towed in the wake of a symmetrical payload at supersonic speeds, in general, had good drag and stability characteristics if towed in the supersonic flow region. A cone with an included angle between 80 and 90 degrees gave 2 maximum drag while still maintaining stability. In order to minimize wake effects, the ratio of cone base diameter to payload base diameter should be at least one and preferably around three. A trailing distance of three times the payload base diameter, in most cases, is of sufficient length to avoid low drag and instability of the decelerator. (Author).
Effects of Cone Angel, Mach Number, and Nose Blunting on Transition at Supersonic Speeds
Author: K. R. CzarneckiPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
The Damping in Pitch and Static Stability of Six Supersonic Impact Ballistic Configurations and Three High-drag Reentry Capsules at a Mach Number of 6.83
Author: Herman S. FletcherPublisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Effects of Cone Angle, Mach Number, and Nose Blunting on Transition at Supersonic Speeds
Author: K. R. CzarneckiPublisher:
ISBN:
Category :
Languages : en
Pages : 31
Book Description
