Hypersonic Reentry Vehicle Wake Flow Fields at Angle of Attack

2006 ◽  
Author(s):  
Tony Lin ◽  
Linda Sproul ◽  
Moon Kim ◽  
M Olmos ◽  
H Feiz
Keyword(s):  
Angle Of Attack ◽  
Flow Fields ◽  
Wake Flow ◽  
Reentry Vehicle

scholarly journals Research on Aeroheating of Hypersonic Reentry Vehicle Base Flow Fields

2017 ◽  
Vol 234 ◽  
pp. 012011
Author(s):  
Qin Xuguo ◽  
Shui Yongtao ◽  
Wang Yonghai ◽  
Chen Gang ◽  
Li Qiang
Keyword(s):  
Flow Fields ◽  
Base Flow ◽  
Reentry Vehicle

Maximum Landing Footprint Calculation Method with Angle of Attack Optimization for Reentry Vehicle

2021 ◽  
pp. 3321-3333
Author(s):  
Chi Fenghua ◽  
Wu Meng ◽  
Li Fei ◽  
Hui Xiangyang ◽  
Teng Rui
Keyword(s):  
Calculation Method ◽  
Angle Of Attack ◽  
Reentry Vehicle

Two-Dimensional Experimental Investigation on the Effects of a Fowler Flap Gap and Overlap Size on the Wake Flow Field

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
David Demel ◽  
Mohsen Ferchichi ◽  
William D. E. Allan ◽  
Marouen Dghim
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Angle Of Attack ◽  
Wake Flow ◽  
Two Dimensional ◽  
Edge Region ◽  
Suction Surface ◽  
Trailing Edge ◽  
Piv Measurements ◽  
Image Velocimetry

This work details an experimental investigation on the effects of the variation of flap gap and overlap sizes on the flow field in the wake of a wing-section equipped with a trailing edge Fowler flap. The airfoil was based on the NACA 0014-1.10 40/1.051 profile, and the flap was deployed with 40 deg deflection angle. Two-dimensional (2D) particle image velocimetry (PIV) measurements of the flow field in the vicinity of the main wing trailing edge and the flap region were performed for the optimal flap gap and overlap, as well as for flap gap and overlap increases of 2% and 4% chord beyond optimal, at angles of attack of 0 deg, 10 deg, and 12 deg. For all the configurations investigated, the flow over the flap was found to be fully stalled. At zero angle of attack, increasing the flap gap size was found to have minor effects on the flow field but increased flap overlap resulted in misalignment between the main wing boundary layer (BL) flow and the slot flow that forced the flow in the trailing edge region of the main wing to separate. When the angle of attack was increased to near stall conditions (at angle of attack of 12 deg), increasing the flap gap was found to energize and improve the flow in the trailing edge region of the main wing, whereas increased flap overlap further promoted flow separation on the main wing suction surface possibly steering the wing into stall.

Boundary Effects in Wake Flow

1968 ◽  
Vol 35 (3) ◽  
pp. 571-578
Author(s):  
C. Y. Liu
Keyword(s):  
Experimental Data ◽  
Flat Plate ◽  
Analytical Solutions ◽  
Angle Of Attack ◽  
Finite Depth ◽  
Wake Flow ◽  
Boundary Effects ◽  
Arbitrary Angle ◽  
Linearized Theory

Analytical solutions are obtained for the problem of boundary effects on the fully developed wake (or cavity) behind an inclined flat plate at an arbitrary angle of attack. The investigation is based on the Helmholtz free-streamline theory. Results are applied to four cases: (a) Blockage in a fixed-wall tunnel, (b) planing on a stream of finite depth, (c) planing toward a waterfall, and (d) flow over a flat plate in a bounded jet. Comparisons with linearized theory and available experimental data are made.

Tomographic PIV investigation on 3D wake structures for flow over a wall-mounted short cylinder

2017 ◽  
Vol 831 ◽  
pp. 743-778 ◽  
Author(s):  
Hang-Yu Zhu ◽  
Cheng-Yue Wang ◽  
Hong-Ping Wang ◽  
Jin-Jun Wang
Keyword(s):  
Aspect Ratio ◽  
Circular Cylinder ◽  
Dynamic Characteristics ◽  
Large Scale ◽  
Low Frequency ◽  
Streamwise Vortex ◽  
Flow Fields ◽  
Vortex Structures ◽  
Wake Flow ◽  
Wake Field

Tomographic particle image velocimetry (TPIV) measurement with six high-resolution charge-coupled device (CCD) cameras is conducted to investigate flow structures over a finite circular cylinder with an aspect ratio of 2 ($h/d=2$). This short wall-mounted cylinder is fully immersed in a thick turbulent boundary layer ($\unicode[STIX]{x1D6FF}/h=1.025$). Focus is placed on the three-dimensional instantaneous vortex structures and their dynamic characteristics in the wake flow fields. Based on the present results, a refined topological model of the mean wake field behind the finite circular cylinder is proposed, where the spatial locations of the typical vortex structures and their interactions are described in more detail. Among the reported typical vortex structures (i.e. the horseshoe, tip, base, trailing and arch vortex), emphasis is laid on discussion of the tip and arch vortex. The instantaneous 3D M-shape arch vortex and an alternating large-scale streamwise vortex are first found in the present experiment, and their developments are also discussed. Therefore, it is suggested that the instantaneous finite-cylinder wake is dominated by the arch vortex system and the large-scale streamwise vortices. Moreover, in the instantaneous volumetric flow fields, both the antisymmetric and the symmetric wake behaviours are observed. With proper orthogonal decomposition (POD) analysis, the dynamic characteristics of the wake field are clarified. Different from the flow around an infinite cylinder without control, the third and fourth POD modes are characterized by low-frequency symmetric shedding. The low-frequency feature shown in the second mode pair is observed and associated with the occurrence of instantaneous symmetric 3D wake behaviour triggered by the low-aspect-ratio effect and the extension of the separated shear layer. The low frequency seems be attributed to the flapping phenomenon, i.e. oscillation of the recirculation in the backward-facing step flow. It is found that the flapping motion has a modulating effect on the occurrence of the antisymmetric shedding vortex and thus the large-scale streamwise vortex.

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