Author: Robert W. CubbisonPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 34
Book Description
Surface Pressure Distributions with a Sonic Jet Normal to Adjacent Flat Surfaces at Mach 2.92 to 6.4
Author: Robert W. CubbisonPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 34
Book Description
Surface Pressure Distributions with a Sonic Jet Normal to Adjacent Flat Surfaces at Mach 2.92 to 6.4
Author: Robert W. CubbisonPublisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Loads Induced on a Flat Plate at a Mach Number of 4.5 with a Sonic Or Supersonic Jet Exhausting Normal to the Surface
Author: William LetkoPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 32
Book Description
Pressure Distributions Induced by Elevon Deflections on Swept Wings and Adjacent End-plate Surfaces at Mach 6
Author: Louis G. Kaufman (II.)Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 132
Book Description
The Flow of Two Adjacent Plane Supersonic Jets Past Flat Plate Wings, IV
Author: Maurice HoltPublisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
Using the general formulae derived earlier (Quart. J. Mech. Appl. Math. IV; 4:419-431, 51) further surface pressure distributions are calculated on delta wings placed in two adjacent uniform supersonic jets. Five cases are considered wh the port et lea ing edge lies outside and the starboard leading edge lies inside the respective Mach semi-cones. (Author).
Pressure distributions induced by elevon deflections on swept wings and adjacent end-plate surfaces at Mach 6
Author: Louis G. KaufmanPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 122
Book Description
Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9
Author: Harold MirelsPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
Book Description
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Pressure Distribution Induced on a Flat Plate by a Supersonic and Sonic Jet Exhaust at a Free-stream Mach Number of 1.80
Author: Abraham LeissPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 61
Book Description
As a continuation of previous research at Mach numbers of 2.02 and 1.39, an experimental investigation was made of the pressures induced on a flat plate by a propulsive jet exhausting from sonic and supersonic nozzles at a free-stream Mach number of 1.80. Measurements of the pressure distribution on a flat-plate wing were made at zero angle of attack for four different locations of the jet exhaust nozzle beneath the wing. Both a choked convergent nozzle and a convergent-divergent nozzle on the nacelle were used. The nozzles were operated at nacelle-exit total-pressure ratios from 2 to 16 and the Reynolds number per foot was approximately 13,000,000.
Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description
An Experimental Investigation of the Surface Pressure Distribution on a Cylindrically Blunted Flat Plate at Mach Numbers of 10 and 16
Author: W. BurggrafPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 0
Book Description
A cylindrically blunted flat plate was tested in the Aerospace Research Laboratories 30-inch hypersonic wind tunnel at M = 16 and at Reynolds numbers from 3,000 to 25,000 based on leading edge diameter. The flat plate was equipped with interchangeable leading edges of 1/8, 1/4, and 1/2 inch diameter to examine this range of Reynolds numbers and to allow pressure measurements to S/D = 100. Angle of attack was varied from 0 to 10 degrees compression for the test sequence. In addition, surface pressure data were obtained on a 1/8 inch thick flat plate in the ALOSU (Aerodynamic Laboratory of The Ohio State University) 12-inch hypersonic wind tunnel at M = 10 and Reynolds numbers ranging from 600 to 1200 based on leading edge diameter. Angle of attack was varied from 10 degrees expansion to 10 degrees compression for the test sequence. (Author).
