Author : William J. Monta
Publisher :
Page : 36 pages
File Size : 39,74 MB
Release : 1971
Category : Aerodynamics
ISBN :
Author :
Publisher :
Page : 1330 pages
File Size : 40,14 MB
Release : 1971
Category : Aeronautics
ISBN :
Author : William A. Corlett
Publisher :
Page : 84 pages
File Size : 37,13 MB
Release : 1966
Category :
ISBN :
Author : M. Leroy Spearman
Publisher :
Page : 36 pages
File Size : 41,59 MB
Release : 1977
Category : Aerodynamics
ISBN :
Author : Earl D. Knechtel
Publisher :
Page : 36 pages
File Size : 35,13 MB
Release : 1956
Category : Charts, diagrams, etc
ISBN :
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.
Author : Edward F. Ulmann
Publisher :
Page : 34 pages
File Size : 34,97 MB
Release : 1954
Category : Ballistic missiles
ISBN :
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.
Author : M. Leroy Spearman
Publisher :
Page : 52 pages
File Size : 33,9 MB
Release : 1967
Category : Guided missiles
ISBN :
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.
Author : William J. Evans
Publisher :
Page : 150 pages
File Size : 46,14 MB
Release : 1964
Category : Aerodynamic load
ISBN :
Six-component force and moment data were obtained for Mach 5 and 8 flows over a blunt pyramidal configuration. The model had a triangular cross section and was composed of two dihedral surfaces and a 70-degree sweepback delta wing lower surface. Three-component force and moment data were obtained on a remotely controlled trailing edge flap at deflections up to 40 degrees. All three surfaces had trailing edge flaps and the model was tested with and without canards and a ventral fin. The model was pitched at angles of attack between ±54 degrees and side-slip angles between -4 and +14 degrees. For both Mach numbers, the data were obtained for a nominal free stream Reynolds number, based on model length, of 4.5 million. Selected configurations were tested at other Reynolds numbers between 1.2 and 9.1 million. (Author)
Author : Frankie Gale Moore
Publisher :
Page : 148 pages
File Size : 17,45 MB
Release : 1997
Category : Aerodynamics
ISBN :
Author :
Publisher :
Page : 60 pages
File Size : 49,50 MB
Release : 1967
Category :
ISBN :
