An Experimental Investigation of the Passive Control of Reverse Delta Wing Vortex Flow Structure and Aerodynamics Characteristics - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of the Passive Control of Reverse Delta Wing Vortex Flow Structure and Aerodynamics Characteristics write by Hongzhi Mou. This book was released on 2016. An Experimental Investigation of the Passive Control of Reverse Delta Wing Vortex Flow Structure and Aerodynamics Characteristics available in PDF, EPUB and Kindle. "This thesis summarises an experimental study of a 65-sweep reverse delta wing (RDW) by using a seven-hole pressure probe and a two-component force balance at Re = 270,000. Dye water flow visualization was also conducted in order to better understand the flow structure. Particular emphasis was placed on the variation of vortex flow quantities and critical flow parameters such as the core circulation, total circulation, tangential velocity and axial core velocity with change in chordwise locations from x/c = 0.2 to x/c = 1.5 for [alpha] = 10°- 22°. Based on lift measurements, the RDW generated less lift from [alpha] = 8° to [alpha] = 35° in comparison with the conventional delta wing (DW). Hence, lift augmentation was attempted by attaching passive control devices such as a side edge strip (SES) and a leading edge strip (LES), made from aluminum strips with different widths, which were placed perpendicularly to the wing's bottom surface. The flow field scans showed that the vortex flow underwent diffusion while it progressed in the chordwise direction. The size of the separated flow region, which originated from the spanwise vortex breakdown, increased with the angle of attack. Compared to a baseline RDW, RDW with SES generated a pair of more concentrated vortices with a higher core and total circulation values. Compared to a baseline RDW, the lift coefficient generated by the RDW with a 1.5% c SES and a 3% c SES increased by 0.18 to 0.28 on average, for angles of attack ranging from 0° to 40°. In addition, 1.5% c and 3% c SES boosted the wing's lift-to-drag ratio, for an average of 24% and 5%, respectively, from angles of attack of 10° to 20°. The dye flow visualization showed that the vortex flow generated by the RDW was located outside of the wing's surface and the vortex generated by the DW is located above the wing surface, in which suggesting the vortex lift is not applicable to a RDW. " --
An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing
An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing write by Lok Sun Ko. This book was released on 2017. An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing available in PDF, EPUB and Kindle. "Reverse or inverted delta wing planforms have been employed extensively in the Lippisch-type wing-in-ground effect (WIG) craft for the past few decades. Despite their industrial applicability and popularity, the aerodynamics and the vortex flowfield generated by the reverse delta wing are, however, not available in archived publications. Extensive experimental investigations utilizing particle image velocimetry, force balances, and dye and smoke-wire flow visualizations were, therefore, conducted in this study to better understand the aerodynamic load generation and the vortex flow structure of a reverse delta wing, both slender and non-slender. The results show that for a reverse delta wing in a free stream the wing stall was delayed and had a lowered lift and drag compared to a regular or conventional delta wing at the same angle of attack. The drag reduction of the reverse delta wing, however, underperformed the decrease in the lift, rendering an improved lift-to-drag ratio compared to the regular delta wing. More importantly, the upper surface flow of the reverse delta wing was found to be characterized by the unique multiple spanwise vortex filaments. In contrast to the leading-edge vortex breakdown-induced stalling of the regular delta wing, the stalling mechanism of the reverse delta wing was found to be triggered by the breakdown of the multiple spanwise vortex filaments. Meanwhile, the reverse-delta-wing vortices were also found to be located outboard, suggesting their irrelevance to the lift generation of the reverse delta wing. The lift of the reverse delta wing was found to be mainly generated by the pressure acting on its lower surface, while the upper surface acts like a wake generator. These two streamwise counter-rotating vortices generated by the reverse delta wing were also found to became nearly axisymmetric at 0.7 chord downstream from the leading edge of the reverse delta wing. For a non-slender reverse delta wing (i.e., with a sweep angle less than 55 deg), the above-mentioned findings were found to remain unchanged but had a much smaller magnitude compared to its slender counterpart.Finally, in order to enhance the lift generation capability of the reverse delta wing, passive Gurney flaplike strips, of different heights and configurations, were applied to both the side edges and the leading edges of the reverse delta wing. The addition of the side-edge strips was found to produce a leftward shift of the lift curve, resembling a conventional trailing-edge flap, and a large lift enhancement. The large lift increment overwhelmed the corresponding drag increase, thereby leading to a further improved lift-to-drag ratio compared to the clean reverse delta wing. The lift and drag coefficients were also found to increase with the strip height. The side-edge strip-equipped wing also produced a strengthened vortex compared to its baseline wing counterpart, while the leading-edge strips were found to persistently produce a greatly diffused vortex flow, which therefore suggests a promising wingtip vortex control alternative. The downward leading-edge strip was found to be capable of delivering a delayed stall and an increased maximum lift coefficient compared to the clean baseline wing. In summary, the present first-of-its-kind experimental findings on the reverse delta wing will not only advance our understanding of the lift and drag generation and the vortex flow characteristics, but can also serve as benchmark data for CFD validation. The present study will also lay a foundation for the study of the effects of ground proximity on the reverse delta wing, and, more importantly, lead to an improved design of wing-in-ground effect craft. " --
Experimental Investigation of the Aerodynamics of a Reverse Delta Wing in Ground Effect Using Passive Control
Experimental Investigation of the Aerodynamics of a Reverse Delta Wing in Ground Effect Using Passive Control - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Experimental Investigation of the Aerodynamics of a Reverse Delta Wing in Ground Effect Using Passive Control write by David Huitema. This book was released on 2018. Experimental Investigation of the Aerodynamics of a Reverse Delta Wing in Ground Effect Using Passive Control available in PDF, EPUB and Kindle. "Wing-in-ground effect craft utilize the lift augmentation and drag reduction experienced by aircraft flying in close proximity to the ground. Several designs use a reverse delta wing with anhedral tips due to improved stability in ground effect, despite the inferior lift generation of this planform limiting its widespread adoption. Also, archived research into reverse delta wings is limited, especially in ground effect. The aerodynamic forces generated by a slender and non-slender reverse delta wing in ground effect was experimentally investigated using force balance measurements in an open return wind tunnel. The impact of anhedral, rear planform cropping and passive control via Gurney flaplike strips was investigated.The results demonstrate that the impact of ground effect on the reverse delta wing was greatest at low angles of attack and ground clearances. Increased lift is in part a result of increased static pressure on the lower surface. Anhedral further increased lift, suggesting the stagnation of high momentum flow beneath the wing resulting in an "air tunnel" like effect and resulting in significant lift increases at low ground clearances and high anhedral angles. The relation between the lift and drag increments in ground effect was found to be approximately linear, with marginal improvement in the lift-to-drag ratio. In the freestream, employment of side-edge strips shifted the lift-curve leftward (induced camber-like effect), resulting from reduced crossflow leakage and increased windward surface pressure. Equipping these strips in ground effect significantly augmented lift with increasing strip height. An increasingly adverse pressure gradient and extension of the side-edge strip beyond the boundary layer led to increased drag with strip height. Rear planform cropping in freestream conditions had a benign impact on aerodynamic forces, while in ground effect increased lift and drag from greater ground proximity, with increased drag suggesting an enhanced disruption of the spanwise vortex filaments. The optimum configuration was found to be a 30% cropped reverse delta wing with 15-degree anhedral, equipped with side-edge strips with height of 4% of the root chord, resulting in significant lift and aerodynamic efficiency improvements alongside weight loss from the cropping. The above findings generally agreed with the results for the non-slender models, with greater force magnitudes observed for the non-slender case. A non-zero lift coefficient was observed at zero incidence for the non-slender wing in ground effect. Further study is required to elucidate the flow mechanisms.The results presented here are first of a kind for a reverse delta wing in ground effect, demonstrating that lift augmentation may be achieved on reverse delta wings operating in ground effect through the utilization of passive control. These results provide benchmark data for further studies on reverse delta wings in and out of ground effect." --
An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings
An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings write by Muneeb Dogar. This book was released on 2013. An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings available in PDF, EPUB and Kindle. "The leading-edge vortical flow structure over a 65 slender (DW65) and a 50 non-slender (DW50) delta wing was investigated at Reynolds number of order 105. Particular emphasis was placed in the variation of vortex flow quantities and critical flow parameters with change in angle of attack and chordwise distance. In addition, the progression of vortex breakdown with angle of attack was documented based on pressure and three-dimensional velocity information. A glimpse of wake-vortex evolution was also discussed. Moreover, aerodynamic lift and drag forces were evaluated based on wake survey analyses and compared with direct force balance measurements. Special attention was focused on drag characterization based on lift dependency where Maskell formulation was adopted for the estimation of induced drag. The results showed that the flow over DW65 and DW50 has some qualitative resemblances but quantitatively they are two contrasting flows. Prior to the breakdown, in the case of DW65, the vortical flow is near-axisymmetric but in the case of DW50, the vortex and axial core never matches and even the definition of distinctive vortex center is often ambiguous except at higher angles of attack, moreover the axial core was always accompanied by large momentum deficit. The variation of vortex flow quantities in streamwise direction showed self-similar behavior when plotted against radial distance scaled by local semi-span while interestingly for DW50 self-similar behavior was showed only by the variation of total pressure loss about the pressure core. It was established that the flow over DW50 was marred by an active interaction of vortical and boundary layer flow due to the close proximity of vortex to the wing surface. For the first time the progression of vortex breakdown over the wing surface was reported on the basis of three-dimensional flow information which elucidated the respective indicators of breakdown for slender and non-slender delta wings. Lastly, wake survey analyses were carried and comparison of different lift computational models and direct measurement were presented. Moreover, the estimation of profile drag is sensitive to the definition of wake region whereas vortex breakdown upstream of trailing-edge resulted in underestimation and overestimation of induced drag and CL, respectively. For all the cases of slender wing and high angle of attack cases of non-slender delta wing showed that the induced drag always constituted more than 50% of the total drag. The results provided here provided a deepened and extended insight on vortical and aerodynamics characteristics of slender and non-slender delta wing. " --
An Experimental Investigation of Wingtip Vortices Generated by a Reverse Delta Wing of Different Wing Configurations
An Experimental Investigation of Wingtip Vortices Generated by a Reverse Delta Wing of Different Wing Configurations - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of Wingtip Vortices Generated by a Reverse Delta Wing of Different Wing Configurations write by Mengyizhe He. This book was released on 2019. An Experimental Investigation of Wingtip Vortices Generated by a Reverse Delta Wing of Different Wing Configurations available in PDF, EPUB and Kindle. "The reverse delta wing (RDW) planform is uniquely seen on the Lippisch-type wing-in-ground effect vehicles that have emerged as a new and sustainable mode of commercial sea travel in the last decade, yet public archives of RDWs are rarely seen and relevant academic studies are scarce. This study investigates wingtip vortices generated by different RDW configurations outside ground effect (GE) as to expand knowledge about RDWs and to establish potential benchmark data for future studies in GE. Flow measurements of 16" in chord 65 ̊-sweep RDW models were obtained using a seven-hole pressure probe at low subsonic speeds and a Reynolds number of 3.3x10^5. Major attention was paid to the streamwise evolution and characteristics of the tip vortices at the angle of attack of 16 ̊. The various wing models were configured with, separately and jointly, trailing-apex cropping, anhedral and winglets. Gurney flaplike strips were also examined as a lift augmentation and passive flow control device. In addition, the lift and drag forces of each configuration were measured via a force balance to supplement the flow-field data. The cropping had a minimal impact on the RDW vortices and aerodynamic forces while the anhedral engendered faster-rotating vortices and minimized lift-induced drag. The side-edge strips enhanced the vortex strength and wing lift, but also drag. The winglets generated a co-rotating vortex pair but kept the vortex strength mostly intact. Lift based on the total vortex circulation underestimated the experimental values by 1.5-11.3%, suggesting that the RDW vortex strength can represent majority of the actual lift. Lastly, induced drag computed using the vorticity flow field constituted 17.6-27.5% of the total drag." --
