Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 60
Book Description
Aerodynamic Characteristics at Mach Numbers of 3.95 and 4.63 for a Missile Model Having All-movable Wings and Interdigitated Tails
Author: Aerodynamic Characteristics at Mach Numbers from 0.40 to 2.86 of a Missile Model Having All Movable Wings and Interdigitated Tails
Author: Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Fixed-span Missile with Three Wing Planforms
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Maneuverable Missile with In-line Cruciform Wings and Canard Surfaces
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 52
Book Description
An investigation has been conducted in the Langley Unitary Plan wind tunnel at Mach numbers from 1.50 to 4.63 to determine the aerodynamic characteristics of a maneuverable missile having in-line cruciform wings and canard surfaces oriented in 45° roll planes.
Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Spanmissile with Three Wing Planforms
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
Book Description
Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.16 of a Blunt-nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins
Author: William J. MontaPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Aerodynamic Characteristics of a Series of Bodies with and Without Tails at Mach Numbers from 0.8 to 3.0 and Angles of Attack from 0 to 45 Degrees
Author: Jimmie N. DerrickPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 896
Book Description
Wind tunnel tests were conducted in a 16 ft. transonic tunnel, a supersonic tunnel, A and a trisonic tunnel to establish a bank of systematic data for body and body-tail configurations at high angles of attack. The configurations were tested at Mach numbers between 0.8 and 3.0, angles of attack from -2 to 45 degrees, and roll angles from 0 to 90 degrees. The aerodynamic characteristics were obtained for the total configuration as well as each of the four undeflected tail fins.
Aerodynamic Characteristics at Mach 1.60, 2.00, and 2.50 of a Cruciform Missile Configuration with In-line Tail Controls
Author: W. A. CorlettAn Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 To 6. 8
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722067939
Category :
Languages : en
Pages : 32
Book Description
A study has been made of the experimental and theoretical aerodynamic characteristics for some generic high-speed missile concepts at Mach numbers from 2 to 6.8. The basic body for this study had a length-to-diameter ratio of 10 with the forward half being a modified blunted ogive and the rear half being a cylinder. Modifications made to the basic body included the addition of an after body flare, the addition of highly swept cruciform wings and the addition of highly swept aft tails. The effects of some controls were also investigated with all-moving wing controls on the flared body and trailing-edge flap controls on the winged body. The results indicated that the addition of a flare, wings, or tails to the basic body all provided static longitudinal stability with varying amounts of increased axial force. The control arrangements were effective in producing increments of normal-force and pitching-moment at the lower Mach numbers. At the highest Mach number, the flap control on the winged body was ineffective in producing normal-force or pitching-moment but the all-moving wing control on the flared body, while losing pitch effectiveness, still provided normal-force increments. Calculated results obtained through the use of hypersonic impact theory were in generally good agreement with experiment at the higher Mach numbers but were not accurate at the lower Mach numbers. Spearman, M. Leroy and Braswell, Dorothy O. Langley Research Center RTOP 505-69-20-01...
Author: Edward J. Ray