4 edition of Skin-friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction found in the catalog.
Skin-friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction
by American Institute of Aeronautics and Astronautics, [National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, D.C, Springfield, Va
Written in English
|Other titles||Skin friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction.|
|Statement||by Jeffrey K. Wideman ... [et al.].|
|Series||[NASA contractor report] -- NASA CR-202617.|
|Contributions||Wideman, J. K., United States. National Aeronautics and Space Administration.|
|The Physical Object|
SKIN FRICTION AND TRANSITION LOCATION MEASUREMENTS ON SUPERSONIC TRANSPORT MODELS ROBERT A. KENNELLY JR. I and AGA M. GOODSELL I Keywords: skin friction, oil-film, interferometry, transition, sublimation, supersonic ABSTRACT Flow visualization techniques were used to obtain both qualitative and quantitative skin friction andCited by: 6. Shock-wave/ boundary-layer interactions have therefore been the subject of extensive research. For the two-dimensional case, numerous mean flow data sets exist, over a wide range of Mach and Reynolds numbers, and for a number of flows detailed turbulence measurements have become by: 7.
Shock-wave/turbulent-boundary-layer interaction compression-ramp flow is a canonical test configuration for statistical turbulence modeling. Extensive experimental data are available, whereas computational data focus mainly on Reynolds-averaged computations employing a wide range of turbulence by: Strong crossflow and swept separation are key aspects of the flow dynamics of 3-D shock wave/boundary layer interactions. This study explores the global surface pressure field beneath the canonical interaction produced by a sharp fin with deflection angle $$15^\circ$$ with a turbulent incoming boundary in a Mach 2 freestream flow. This corresponds to an interaction of moderate Author: Lee J. Mears, Andrew Baldwin, Mohd Y. Ali, Rajan Kumar, Farrukh S. Alvi.
Although there is some overlap, the work does not supersede the excellent book by R. C. Dean et al., Aerodynamic Measurements, since some topics are covered in greater detail in Dean’s book. There is a comprehensive list of references, including the complete list taken from Dean’s book, but the index is Author: Julian D. Cole. Anderson, J.: Fundamentals of Aerodynamics: My standard book for aerodynamics. Fairly easy to read. Section briefly covers SBLI. Schülein, E.: Skin-Friction and Heat Flux Measurements in Shock/Boundary-Layer Interaction Flows This paper shows the skin friction along an SBLI for different shock intensities. It provides schlieren images and.
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Enclosed are five copies of the manuscript entitled Skin-Friction Measurements in a 3-D, Supersonic Shock-Wave/Boundary-Layer Interaction, by J.
Widman, J. Brown, J. Miles, O. Ozcan, which Ames Research Center wishes to submit to the AIAA Journal. This manuscript is not classified and has not been submitted elsewhere.
Attached is a File Size: KB. Skin-friction measurements in three-dimensional, supersonic shock-wave/boundary-layer interaction. Progress in shock wave/boundary layer interactions. Progress in Aerospace Sciences, Vol.
Skin-friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction Cited by: Skin-friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction. The 3-D flowfield in a supersonic shock boundary layer corner interaction. PAUL BATCHO and.
An experimental study has been conducted in a three-dimensional, supersonic shockwave/boundary-layer interaction (3-D SW/BLI) with the intent of providing accurate experimental data for turbulence modeling and computational fluid dynamics (CFD) code validation.
The experiment was performed in the High Reynolds Channel 1 (HRCI) wind tunnel at NASA Ames Research : Skin-friction measurements in a 3-D Kenneth Wideman. Get this from a library.
Skin-friction measurements in a 3-D, supersonic shock-wave/boundary-layer interaction: 32nd Aerospace Sciences Meeting & Exhibit, January/Reno, NV. [Jeffrey K Wideman; United States. National Aeronautics and Space Administration.;]. Skin-Friction Measurements in a 3-D, Supersonic Shock-Wave/Boundary-Layer Interaction.
By O. Ozcan, J. Wideman, J. Brown and J. Miles. Abstract. The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 cylinder, aligned with the free-stream flow, and 20 deg.
half-angle conical Cited by: 2. Skin friction measurements by laser interferometry in swept shock/boundary-layer interactions. Skin Friction Measurements Using Oil Film Interferometry in a 3-D Supersonic Flowfield.
Andrew Baldwin, supersonic shock-wave/boundary-layer by: Skin Friction and Heat Flux Measurements in Shock/Boundary Layer Interaction Flows. Erich Schülein ; Erich Schülein. DLR, German Aerospace Center, Gottingen, Germany. Skin Friction Measurements Using Oil Film Interferometry in a 3-D Supersonic by: As an example, Fig.
4(a), (b) and 4(c) display schlieren images of shock wave boundary interactions categorized as laminar, transitional, and turbulent, respectively.
The shock wave boundary layer interaction in Fig. 4(a)–(b) was created by a shock generated by a 4 ∘ wedge. The boundary layer in Fig. 4(a) is laminar throughout the interaction. The incident shock, growth of the boundary Cited by: 6. Introduction.
Shock-wave boundary layer interactions (SBLI) occur in all practical transonic, supersonic and hypersonic one of the earliest reviews on the subject, Green identifies four important situations: transonic aerofoils, high-speed inlets, nozzles at off-design conditions, and near control flaps.
This paper examines the last three, where typically the boundary layer Cited by: The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 cylinder, aligned with the free-stream flow, and 20 deg. half-angle conical flare offset cm from the cylinder centerline.
Surface oil flow, laser light sheet illumination, and schlieren were used to document the flow topology. Fig. Supersonic flow through a sharp concave corner: The flow is from left to right at a downstream Mach number of The holographic interferogram shows flow turning through an angle of 11° thereby forming an oblique shock wave that interacts with the turbulent boundary layer present on the wall.
The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 flow is presented. The model consisted of a sting-supported cylinder, aligned with the free-stream flow, and a 20 deg half-angle conical flare offset cm from the cylinder centerline.
Surface oil flow, laser light sheet illumination and schlieren were used to document the flow Cited by: 2.
Shock-wave/boundary-layer interactions (SWBLI) are of great importance in supersonic transport vehicles. The shock-induced separation and its unsteadiness may lead to harmful influences on the aerodynamic performance and fatigue life of supersonic air-intakes, turbo-machine cascades and supersonic nozzles.
We particularly focus on a three-dimensional SWBLI in supersonic Author: Weipeng Li. Turbulence model assessment for shock wave/turbulent boundary-layer interaction in transonic and supersonic flows.
Skin friction coefficient distributions for impinging oblique shock flow. Direct Measurements of Wall Shear Stress by Buried Wire Gages in a Shock Wave—Boundary Layer Interaction Region, AIAA paperGoogle Cited by: The application of oil film interferometry (OFI) for the measurement of global skin friction on the surface beneath a complex three-dimensional supersonic flow is explored in this study.
The flowfield is produced by a fin-generated oblique shock interacting with a compressible turbulent boundary by: 2. Introduction. Research in the field of high-speed aerodynamics is centred on shocks and their interactions that alter the flowfield.
These alterations affect the forces and heat loads on bodies under consideration.A topic of great importance and interest in this regard is shock wave boundary layer interaction (SWBLI), which essentially deals with inviscid-viscous by: Direct numerical simulations of incident shock wave and supersonic turbulent boundary layer interactions near an expansion corner are performed at Mach number M ∞ = and Reynolds number Re ∞ = to investigate the expansion effect on the characteristic features of this phenomenon.
Four expansion angles, i.e. α = 0 0 (flat-plate), 2 0, 5 0 and 10 0 are : Fulin Tong, Fulin Tong, Xinliang Li, Xianxu Yuan, Changping Yu. Skin friction coefficients between were measured dependent on the facility and measurement location.
Analysis of the measurement uncertainties indicate an accuracy to within + or. BOUNDARY LAYER INTERACTIONS A.A. Zheltovodov, A.I. Maksimov EOARD Contract FWE FINAL REPORT FOR THE PERIOD APRIL -APRIL Novosibirsk pßfw-ot-is~m. the upstream end of the interaction region at the higher upstream Mach numbers.
It is also shown l~ow the skin friction may be roughly predicted. Section combines the results of Sections and to predict the pressure distribution at the wall upstream of the shock. Section gives a very.3-D for brevity) shock wave/boundary-layer interactions. Early studies began with analyt ical and experimental research in 2-D interactions.
Recently, there have been significant advances in 3-D interaction measurements. and by a newer technique - computational studies.Schülein, E., Zheltovodov, A.
A. (). Documentation of Experimental Data for Hypersonic 3-D Shock Waves/Turbulent Boundary Layer Interaction Flows.
DLR, German Aerospace Center. Schülein, E. (). Skin Friction and Heat Flux Measurements in Shock/Boundary Layer Interaction Flows. AIAA Journal, 44(8), doi: /