Author: William J. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Fixed-span Missile with Three Wing Planforms
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Aerodynamic Characteristics of 0.187-scale Model of a Target Missile at Mach 1.80 to 2.16
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 Spearman
Publisher:
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.
Publisher:
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.
Aerodynamic Characteristics at Mach Numbers of 3.95 and 4.63 for a Missile Model Having All-movable Wings and Interdigitated Tails
Aerodynamic Characteristics at Mach Numbers from 0.40 to 2.86 of a Missile Model Having All Movable Wings and Interdigitated Tails
Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4
Author: Earl D. Knechtel
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 36
Book Description
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 36
Book Description
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Normal Force, Center of Pressure, and Zero-lift Drag of Several Ballistic-type Missiles at Mach Numbers of 4.05
Author: Edward F. Ulmann
Publisher:
ISBN:
Category : Ballistic missiles
Languages : en
Pages : 34
Book Description
Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.
Publisher:
ISBN:
Category : Ballistic missiles
Languages : en
Pages : 34
Book Description
Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.
Effects of Nose Bluntness on Aerodynamic Characteristics of Cruciform-finned Missile Configuration at Mach 1.50 to 2.86
An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies
Author: Frankie Gale Moore
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 148
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 148
Book Description