On The Near Flow Field Generated By The Supersonic Flow Over Rearward Facing Steps
Download On The Near Flow Field Generated By The Supersonic Flow Over Rearward Facing Steps full books in PDF, epub, and Kindle. Read online free On The Near Flow Field Generated By The Supersonic Flow Over Rearward Facing Steps ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author | : Jain-Ming Wu |
Publisher | : |
Total Pages | : 161 |
Release | : 1971 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Measurements were made and evaluated in the oncoming boundary layer, in the free shear layer, the lip shock and in the wake (or reattachment) shock region. Pitot and static pressure surveys were conducted, along with hot wire measurements and flow visualization studies. The measured free shear layer profiles were compared at different free stream Mach numbers, Reynolds numbers and step heights. A new technique was established for reducing the hot wire data. This was based upon the heat transfer correlation formula, and allows a broader range of applicability; in both the low Reynolds number region and in the free shear layer where the flow field is changing rapidly. This technique when applied to the measurements allowed the flow structure in the recirculating region to be explored. The low base pressure generated by the step influences the flow field ahead of the step and the extent of this upstream influence has been discussed. A new base pressure correlation parameter has also been developed for fully laminar and transitional flow.
Author | : Albert L. Waters |
Publisher | : |
Total Pages | : 77 |
Release | : 1969 |
Genre | : |
ISBN | : |
The supersonic flow field over a rearward facing step was studied with a schlieren system. The effect of Mach number variation, step height variation, and total pressure variation on the expansion fan angle, lip shock angle, flow turning angle, reattachment point, and reattachment shock angle was determined. Schlieren photographs of the flow at Mach number 2.7 to 3.1, step heights of 1/4 to 3/4 in, and total pressures of 60 to 95 psia are presented. It was found that the relatively small changes in Mach number had the smallest effect on the flow field and that changing the step height had the greatest effect on the flow field. The flow turning angle was sensitive to all three variables.
Author | : Howard E. Smith |
Publisher | : |
Total Pages | : 82 |
Release | : 1967 |
Genre | : Gas flow |
ISBN | : |
Author | : Michael Wen-Shean Su |
Publisher | : |
Total Pages | : 142 |
Release | : 1970 |
Genre | : |
ISBN | : |
Author | : Odus R. Burggraf |
Publisher | : |
Total Pages | : 56 |
Release | : 1970 |
Genre | : |
ISBN | : |
The problem of laminar separated flow over a backward-facing step is solved numerically for the limiting case of infinite Reynolds number. The flow model adopted is that deduced by Batchelor for incompressible flow: an inviscid rotational eddy confined within the recirculation portion of the separated shear layer. It is argued that the reattachment process is essentially inviscid in the limit R approaches infinity, and the flow field in the reattachment zone is computed on this basis. The computed results support Chapman's model of the reattachment process as the correct limit case, to second-order accuracy, as the flow angle entering the reattachment zone approaches zero. For the recirculation zone, the boundary-layer equations are simplified by assuming a constant pressure eddy. The Dorodnitsyn transformation is applied and numerical solutions obtained using an implicit finite-difference scheme. The solutions are carried out from station-to-station in the direction of flow over a complete cycle of recirculation. Iteration yields the unique value of the vorticity in the inviscid layer upstream of separation, including the effects of corner expansion and recirculation on the development of the separated shear layer. (Author).
Author | : |
Publisher | : |
Total Pages | : 592 |
Release | : 1983 |
Genre | : Astronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 958 |
Release | : 1972 |
Genre | : Aeronautics |
ISBN | : |
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author | : Donald R. Crawford |
Publisher | : |
Total Pages | : 166 |
Release | : 1967 |
Genre | : |
ISBN | : |
The method of integral relations is applied to the study of the viscous separated flow field downstream of a backward facing step in laminar supersonic flow. The boundary layer equations are reduced to a set of coupled ordinary differential equations in a formulation which incorporates a two parameter velocity profile. The neighborhood of the corner and the reattachment point are examined in detail, taking into account the proper interaction between the viscous and inviscid flow. The complete flow field in these regions is found from the analyses of the limiting forms of the equations. In particular, it is found that the pressure gradient and thickness of the boundary layer at the reattachment point are related and cannot be arbitrarily specified. (Author).
Author | : Albert L. Waters (CAPT, USAF.) |
Publisher | : |
Total Pages | : 64 |
Release | : 1969 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Eric Loth |
Publisher | : |
Total Pages | : |
Release | : 1990 |
Genre | : |
ISBN | : |