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Tuesday, July 21, 2020 | History

2 edition of study of the sonic-boom characteristics of a blunt body at a Mach number of 6 found in the catalog.

study of the sonic-boom characteristics of a blunt body at a Mach number of 6

George C. Ashby

# study of the sonic-boom characteristics of a blunt body at a Mach number of 6

## by George C. Ashby

Subjects:
• Sonic boom.,
• Aerodynamics, Supersonic.

• Edition Notes

The Physical Object ID Numbers Statement George C. Ashby, Jr. Series NASA technical paper -- 1787. Contributions United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., Langley Research Center. Pagination 31 p. : Number of Pages 31 Open Library OL17542260M

In aerodynamics, a hypersonic speed is one that greatly exceeds the speed of sound, often stated as starting at speeds of Mach 5 and above.. The precise Mach number at which a craft can be said to be flying at hypersonic speed varies, since individual physical changes in the airflow (like molecular dissociation and ionization) occur at different speeds; these effects collectively become.   Wind-tunnel investigation of sonic-boom characteristics of two simple wing models at mach numbers from to David S. Miller, Odell A. Morris, Harry W. Carlson. TN D Aerodynamic characteristics at mach numbers from to of a blunt-nose missile model having a triangular cross section and fixed triform fins. William J Center: Langley Research Center.

testing of its Shaped Sonic Boom Demonstrator (SSBD). Benson begins by explaining the science behind the cause of the sonic phenomenon known as a sonic boom. He discusses early research, beginning with Austrian physicist/philosopher Ernst Mach, who explained the concept of sonic booms. Mach determinedCited by: 3. Full text of "NASA Technical Reports Server (NTRS) Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley inch Hypersonic Tunnel at a Mach Number of " See other formats NACA TN NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS TECHNICAL NOTE INVESTIGATION OF THE LAMINAR AERODYNAMIC HEAT -TRANSFER CHARACTERISTICS .

The present chapter deals with heat transfer analysis around unspiked and spiked bodies at high speeds. A spike attached to a blunt-nosed body drastically alters its flowfield and influences the aerodynamic heating in a high speed flow. The effect of spike length, shape and spike-nose configuration is numerically studied at zero angle of by: 1.   The courant number should be given considering the mach number and the mesh quality for the simulation. The courant number should be reduced with increase in the mach number value. The courant number window is shown in below fig (f) Fig (f) Solution controls

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### Study of the sonic-boom characteristics of a blunt body at a Mach number of 6 by George C. Ashby Download PDF EPUB FB2

The sonic-boom pressure signatures parallel to the axis of a blunt body were measured at several fixed distances from the axis at Mach 6. A finite- difference computer program was used to compute the signatures at Mach numbers 4 and 6 for comparison with experimental data at Author: George C.

Ashby. A Study of the Sonic-Boom Characteristics of a Blunt Body at a Mach Number of Harry W. Carlson and Robert J. Mack Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Scientific and Technical InformationOffice Get this from a library.

A study of the sonic-boom characteristics of a blunt body at a Mach number of 6. [George C Ashby; United States.

National Aeronautics and Space Administration. Scientific and Technical Information Branch.; Langley Research Center.]. A study of the sonic-boom characteristics of a blunt body at a Mach number of 6 / By George C.

Ashby, Langley Research Center. and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

“ A Study of the Sonic-Boom Characteristics of a Blunt Body at a Mach Number of 6,” NASA TPGoogle Scholar [47] Moss J. N., Glass C.

and Greene F. A., “ DSMC Simulations of Apollo Capsule Aerodynamics for Hypersonic Rarefied Conditions,” 9th AIAA/ASM Thermophysics and Heat Transfer Conference, AIAA Paper Author: Jean Varnier, Marie-Claire Le Pape, Frédéric Sourgen. pound, foot-long aircraft flying at a Mach number of 3 and an altitude of 70 feet has an overpressure level of pounds per square foot.

Yet if the pressures on the ground were distributed appropriate theory is essential in a study of sonic boom.

The phenomenon of sonic boom is well described by a theory of quasilinear geometrical File Size: 4MB. An experimental investigation was performed to measure aerodynamic forces for spikes blunt bodies with a conical, hemispherical and flat-face spike at Mach 6 and at an angle-of-attack range from 0.

The use of CFD to study this region is advantageous as experimental studies are unable to take many measurements without being intrusive. This paper investigates the effect of the dynamic jet shape on the bow shock stand-off distance and shape using contemporary CFD methods. The shock wave characteristics in the shock layer are also by: 3.

Blunt body calculations at Mach numbers of greater than 15 are performed to treat real-gas effects, and impinging shock results are obtained to test the treatment of slip surfaces and complex. Full text of "Damping in pitch and static stability of a group of blunt-nose and cone-cylinder-flare models at a Mach number of " See other formats I CO I LO M L L C • ^ %' I^^^O A^ LOAN COPY; AFVVL KIRTLAi'JD MEMORANDUM -1 m o X r- S LJ J] tr ru — i a •• U ' z 3 7D DAMPING IN PITCH AND STATIC STABILTTY OF A GROUP OF BLUNT -NOSE AND CONE.

Benchmark CFD Study of Spiked Blunt Body Configurations range of attack angles at a Mach number of A blunt body, a classical disk-tip spike, a sphere-tip spike, and a biconical-tip spike Author: Roberto Roveda. Study of the sonic-boom characteristics of a blunt body at a Mach number of [Washington]: National Aeronautics and Space Administration, Scientific and.

Testing were done at MachRe number of x 10 6 (based on chord), from α = –12 ° to 12 ° and flap angle of 20 °, 30 ° and 40°. Separation lengths, measured from Schlieren pictures, clearly show that there is ‘no appreciable’ effect of sweep on by: 4.

The variable blunt radii method is very useful to improve the whole characteristics of blunt waverider and the L/D can improve 3%. of the blunt body [6], opposing jet in the stagnation zone of.

The motion and the Mach number were chosen to match a maneuver flight of an actual missile: pitching frequency f = Hz, Mach number M =range of angle of attack 0deg.

A sonic boom is the sound associated with the shock waves created whenever an object travels through the air faster than the speed of booms generate enormous amounts of sound energy, sounding similar to an explosion or a thunderclap to the human ear.

The crack of a supersonic bullet passing overhead or the crack of a bullwhip are examples of a sonic boom in miniature. eral basic wing and blunt-body reentry shapes are presented along with some estimates made by the modified Newtonian and shock-expansion the- ories.

Experimental data were obtained from an investigation made in the Langley inch hypersonic tunnel at a Mach number of through an angle-of-attack range up to goo. Abstract. There exist various criteria to be satisfied by the free stream Mach number $$M_{\infty }$$, which makes the flow to be classified hypersonic when it is very high ing on the value of the Mach number, we have hypersonic aerodynamics determined by a predominant parameter with which the flow physics does not change.

a) Mach numbers at which supersonic linear theory fails b) Where γ is no longer constant, and we must consider temperature effects on fluid properties.

c) Mach numbers from 3 - 5, where Mach 3 might be required for blunt bodies causing large disturbances to the flow, and Mach 5 might be the starting point for more highly streamlined Size: 1MB. However, with the increase of bluntness parameter, the overpressure on the ground decreases first and then rises, and the sonic boom impulse shows the similar trend as the overpressure when the Mach number is between andbut for Mach number of tothe impulse increases near linearly with the increasing of the bluntness Author: Lengyan, Qian Zhansen.

Romeo, D.J. and J.R. Sterrett: Exploratory Investigation of the Effect of a Forward-Facing Jet on the Bow Shock of a Blunt Body in a Mach Number 6 Free Stream, NASA TN D Author: Andrew F. Charwat.aircraft Mach number aircraft cutoff Mach number below which sonic boom will not reach ground aircraft effective Mach number governing sonic-boom atmosphere propagation characteristics exponent of Mach number parameter in atmospheric distance factor curve fit (see eq.

(12)) exponent of Mach number parameter in atmospheric pressure ampli.The relative Mach numbers in flat plate supersonic wake flows are then relatively low—on the order of a maximum of (Gai et al., ).

For example, at a free stream Mach number of (see Nakagawa & Dahm, ), the convective Mach number is at x / θ = 60 and as low as at x / θ = (θ is the momentum thickness of the wake.