1 edition of Development of a three-dimensional supersonic inlet flow analysis found in the catalog.
Development of a three-dimensional supersonic inlet flow analysis
Published
1980
by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
.
Written in English
Edition Notes
| Statement | R.C. Buggeln ... [et al.] ; prepared for Lewis Research Center under contract NAS3-21003 |
| Series | NASA contractor report -- 3218 |
| Contributions | Buggeln, R. C, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Lewis Research Center |
| The Physical Object | |
|---|---|
| Pagination | iii, 119 p. : |
| Number of Pages | 119 |
| ID Numbers | |
| Open Library | OL14930434M |
Konrad, W., Smits, A., and Knight, D., ``A Combined Experimental and Numerical Study of a Three-Dimensional Supersonic Turbulent Boundary Layer'', Second International Symposium on Engineering Turbulence Modelling and Measurements, Florence, Italy, May June 2, Development of the Nano Hummingbird: A Tailless Flapping Wing Micro Air Vehicle Inlet Flow Control Technology: Learning from History, Reinventing the Future. Particle Image Velocimetry of a Three-Dimensional Supersonic Cavity Flow. Beresh, S. / Wagner.
THREE DIMENSIONAL BOUNDARY LAYER TRANSITION ANALYSIS IN SUPERSONIC FLOW USING A NAVIER-STOKES CODE (NS) analysis are summarized in section 2. The results of transition analysis on the sharp cone, the nose cone, and the natural laminar flow wing of the experimental airplane are described in section 3, 4 and 5 respectively. The Scramjet Engine - by Corin Segal June Introduction. With the broad range of flying conditions in the hypersonic regime, the processes in the supersonic combustion chamber are subject to large variations in thermodynamic by: 4.
Steady-state Analysis of Supersonic Mixing Enhanced by a Threedimensional Cavity Flow-(a) duct with a rectangle cavity (b) duct with a three-dimensional cavity pressure gradient across the bow shock wav. Fig. 4: Oil flow visualization16). Fig. 5: Limiting streamlines on the duct lower wall. transversely into the primary flow. The coordinate. The conceptual study by the Boeing Company suggests a two-dimensional inlet as an option (Ref. 1). In addition to external compression of supersonic flow about axisymmetric or two-dimensional surfaces, it is possible to compress supersonic flow about “three-dimensional” surfaces through the process of streamline tracing.
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Development of a three-dimensional supersonic inlet flow analysis. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va.: For sale by the National Technical Information Service], Development of a Three-Dimensional Supersonic Inlet Flow Analysis R.
Buggeln, H. McDonald, R. Levy, and J. Kreskovsky Scierztifc Research Associates, Inc. Glustozzbury, Connecticut Prepared for Lewis Research Center under Contract NAS National Aeronautics and Space Administration Scientific and Technical.
Flow simulation of coupled supersonic inlet-fan. Flow simulations of a coupled supersonic inlet-fan configuration were conducted for a cruise flight condition: Mach numberan altitude of ft (1 ft = m), and an angle of attack of 0 °.A Fortran code was written, which uses shape and performance parameters to build the axisymmetric mixed compression supersonic Cited by: 2.
A Numerical Analysis on Three-Dimensional Flow Field in a Supersonic Bump Inlet Article in Journal of Mechanical Science and Technology 21(2) January with 34 Reads.
inlet geometry and perform analysis of an inlet using a small set of key input factors. The methods used are analytic, empirical, and numerical. While some compressible flow relations and method of characteristics solutions yield planar flow fields, much of the analysis is based on a one-dimensional representation of the inlet flow.
Thus,File Size: KB. The characteristic of a supersonic inlet system with three-dimensional bump which is substituted for the diverter or conventional ramp-type compression systems has been studied numerically. A comprehensive numerical analysis has been performed to understand the threedimensional flow field including shock/boundary layer interaction and growth of turbulent Cited by: 5.
Abstract. The results of designing and numerical gas-dynamic modeling a supersonic three-dimensional inlet of a new type are considered. A ramp of external compression of this inlet is the V-shaped body forming an initial plane oblique shock wave and a subsequent isentropic compression by: 5.
PDF | Turbines operating with supersonic flows offer a potential reduction of the power plant size as a result of the increase in specific mass flow | Find, read and cite all the research you.
A supersonic inlet has two parts. The supersonic diffuser for supersonic and the subsonic diffuser, it is long and heavy. The designer needs to know the size of the inlet in order to properly account for it during the conceptual and preliminary design stage.
The designer also needs to estimate the total pressure recovery at the engine face in. Three Dimensional Interaction Flow Field in a Supersonic Inlet like Configuration. Three Dimensional Interaction Flow Field in a Supersonic Inlet like Configuration at Mach 4 19th 20th Mar 3rd Wind tunnel testing conference.
DRDL, Hyderabad. Also addressed are: three-dimensional flow analysis of turboprop inlet and nacelle configurations, application of computational methods to the design of large turbofan engine nacelles, comparison of full potential and Euler solution algorithms for aeropropulsive flow field computations, subsonic/transonic, supersonic nozzle flows and nozzle.
The basic flow field is usually a steady inviscid supersonic flow one, which is the core of the design of a waverider. Basic flow fields used for waverider design can be classified into two types: steady two-dimensional (2D) planar or asymmetrical supersonic flow fields and three-dimensional (3D) supersonic flow : Yao Zheng, Shuai Zhang, Tianlai Gu, Meijun Zhu, Lei Fu, Minghui Chen, Shuai Zhou.
@article{osti_, title = {Development of finite disturbances in three dimensional Couette flow or the transition to turbulence}, author = {Roy, S.R.}, abstractNote = {The three-dimensional, viscous, incompressible Navier-Stokes system of equations was solved in Couette flow geometry using the velocity and vorticity as dependent variables.
Slater, J.W., “Verification Assessment of Flow Boundary Conditions for CFD Analysis of Supersonic Inlet Flows”, AIAA PaperJuly Slater, J.W. and G.C. Paynter, “Implementation of a Compressor Face Boundary Condition Based on Small Disturbances,” ASME Journal of Turbomachinery, Vol.
April Also NASA TM Thin Airfoil Theory in Supersonic Flow Simple expressions can be derived for the lift and drag coefficients of an airfoil in supersonic flow if the thickness and angle of attack are small. Under these circumstances the pressure disturbances caused by the airfoil are small, and the total flow can be built up by superposition of small.
On the Design of Hypersonic Inward-Turning Inlets Capt. Barry. Croker, Deputy Chief Computational analysis of the JAWS inlet design was performed for three reasons: to verify the design The first step towards design verification was to create three-dimensional models of the inlet geometry based.
Supersonic impinging jet flows always occur when aircrafts start short takeoff and vertical landing from the ground. Supersonic flows with residues produced by chemical reaction of fuel mixture have the potential of reducing aircraft performance and landing ground.
The adverse flow conditions such as impinging force, high noise spectrum, and high shear stress always take Author: Guang Zhang, Guang Fei Ma, Heuy Dong Kim, Zhe Lin.
CHARACTERIZATION OF A SUPERSONIC WIND TUNNEL FOR THE mix the free stream and boundary layer flow. Three dimensional bumps have also been used to Oblique shock waves are formed when the inlet forces the flow to turn on itself, thereby generating a shock.
In an internal flow, these waves will impinge on a surface and reflect. Full text of "Verification Assessment of Flow Boundary Conditions for CFD Analysis of Supersonic Inlet Flows" See other formats NASA/TM-~~ AIAA Verification Assessment of Flow Boundary Conditions for CFD Analysis of Supersonic Inlet Flows John W.
Slater Glenn Research Center, Cleveland, Ohio August The NASASTI Program Office. This study involves computational analysis of NACA flush inlet at high subsonic and supersonic mach regimes in order to verify different flow characteristics like mass flow rate, mass flow ratio and pressure recovery.
Serious CFD analysis first requires verification specially if the problem is highly complex such as turbulent / compressible Size: 1MB. reach the flow conditions required in the combustion chamber but merely the deceleration of the flow in the inlet section, and, in contrast to a regular ramjet, that combustion takes place at supersonic speeds.
This poses strong requirements on the design of the inlet as it has the task of supplying the airflow at the conditions required for super-File Size: 1MB.ramped inlet and an adjustable cone for axisymmetric or semi-axisymmetric inlets. Figure 1 shows a 2D variable structured supersonic ramped inlet of a ghter aircraft, F [6].
The supersonic ramped inlet is one of the most common types of inlet due to its simplicity in design and analysis. The inlet is designed with multiple and. On this web page, we show a method for determining the supersonic flow past a cone.
The method was first developed by G.I. Taylor and J.W. Maccoll in The derivation of the differential equation shown on the slide is fairly complicated. The method assumes that the supersonic flow along a cone is simplified because of symmetry considerations.
