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An Experimental Investigation Of Delta Wing Vortex Flow With And Without External Jet Blowing
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Book Synopsis An Experimental Investigation of Delta Wing Vortex Flow with and Without External Jet Blowing by : Kenneth P. Iwanski
Download or read book An Experimental Investigation of Delta Wing Vortex Flow with and Without External Jet Blowing written by Kenneth P. Iwanski and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Vortex Flow Over a Delta Wing with and Without External Jet Blowing by : Kenneth P. Iwanski
Download or read book An Investigation of the Vortex Flow Over a Delta Wing with and Without External Jet Blowing written by Kenneth P. Iwanski and published by . This book was released on 1988 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Vortex flow and vortex breakdown above a delta wing in high supersonic flow by : Sharon Rose Donohoe
Download or read book Vortex flow and vortex breakdown above a delta wing in high supersonic flow written by Sharon Rose Donohoe and published by . This book was released on 1996 with total page 209 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Flow Fields about Delta and Double-delta Wings at Low Speeds by : William H. Wentz (Jr.)
Download or read book An Experimental Investigation of the Flow Fields about Delta and Double-delta Wings at Low Speeds written by William H. Wentz (Jr.) and published by . This book was released on 1966 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Vortex Flow Over Delta and Double-Delta Wings at Low Speed by : N. G. Verhaagen
Download or read book An Experimental Investigation of the Vortex Flow Over Delta and Double-Delta Wings at Low Speed written by N. G. Verhaagen and published by . This book was released on 1983 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was performed to study, by employing a laserlight-sheet and oil-flow visualization technique, the flow above and behind a sharp-edge 76 deg, delta wing and two sharp-edged double-delta wing models (76/60 and 76/40 deg., kink at midcord). In addition, balance measurements were performed to determine lift, drag and pitching moment. The tests were carried out for angles of attack from 5 to 25 deg. and at a free-stream velocity of 30 m/sec, corresponding to a Reynolds number of 1400000 x 10 to the 6th power, based on centerline chord. Above both double-delta wings a single-branched strake vortex is formed fed by vorticity from the strake leading edge. Downstream of the leading-edge kink a wing vortex is formed which is conjectured to be single-branched at about 5 deg, angle of attack and double branched at angles of 10 deg., an beyond. The flow pattern downstream of the trailing edge of the 76/60 deg. double-delta wing has been observed to be similar to that behind the delta wing. Above the 76/40 deg. double-delta wing breakdown of both the wing and strake vortices took place ahead of the trailing edge. (Author).
Book Synopsis An Experimental Investigation of the Passive Control of Reverse Delta Wing Vortex Flow Structure and Aerodynamics Characteristics by : Hongzhi Mou
Download or read book An Experimental Investigation of the Passive Control of Reverse Delta Wing Vortex Flow Structure and Aerodynamics Characteristics written by Hongzhi Mou and published by . This book was released on 2016 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "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. " --
Book Synopsis Masters Theses in the Pure and Applied Sciences by : Wade H. Shafer
Download or read book Masters Theses in the Pure and Applied Sciences written by Wade H. Shafer and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt: Masters Theses in the Pure and Applied Sciences was first conceived, published, and disseminated by the Center for Information and Numerical Oata Analysis and Synthesis (CINOAS) * at Purdue. University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the activity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all con cerned if the printing and distribution of the volumes were handled by an interna tional publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Cor poration of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 33 (thesis year 1988) a total of 13,273 theses titles from 23 Canadian and 1 85 United States universities. We are sure that this broader base for these titles reported will greatly enhance the value of this important annual reference work. While Volume 33 reports theses submitted in 1988, on occasion, certain univer sities do report theses submitted in previous years but not reported at the time.
Book Synopsis An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing by : Lok Sun Ko
Download or read book An Experimental Investigation of the Aerodynamics and Vortex Flowfield of a Reverse Delta Wing written by Lok Sun Ko and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "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. " --
Book Synopsis Experimental and Numerical Investigation of the Vortex Flow Over a Sharp Edged Delta Wing; with and Without Sideslip by : S. H. J. Naarding
Download or read book Experimental and Numerical Investigation of the Vortex Flow Over a Sharp Edged Delta Wing; with and Without Sideslip written by S. H. J. Naarding and published by . This book was released on 1988 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Leading Edge Vortices and Passage to Stall of Nonslender Delta Wings by :
Download or read book An Experimental Investigation of Leading Edge Vortices and Passage to Stall of Nonslender Delta Wings written by and published by . This book was released on 2003 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings by : Muneeb Dogar
Download or read book An Experimental Investigation of Aerodynamics and Flow Characteristics of Slender and Nonslender Delta Wings written by Muneeb Dogar and published by . This book was released on 2013 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "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. " --
Book Synopsis Numerical Study of Delta Wing Leading Edge Blowing by : David Yeh
Download or read book Numerical Study of Delta Wing Leading Edge Blowing written by David Yeh and published by . This book was released on 1988 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 512 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Leading-edge Vortices on Delta Wings with Jet Blowing by : Z. Shi
Download or read book An Investigation of Leading-edge Vortices on Delta Wings with Jet Blowing written by Z. Shi and published by . This book was released on 1987 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Characterization and Control of Vortex Breakdown Over a Delta Wing at High Angles of Attack by : Anthony M. Mitchell
Download or read book Characterization and Control of Vortex Breakdown Over a Delta Wing at High Angles of Attack written by Anthony M. Mitchell and published by . This book was released on 2000-08-01 with total page 380 pages. Available in PDF, EPUB and Kindle. Book excerpt: Demands for more maneuverable and stealthy air vehicles have encouraged the development of new control concepts for separated flows. The goalof this research is the control of leading-edge vortex breakdown by open-loop, along-the-core blowing near the apex of a delta wing to improve lift and maneuverability at high angles of attack. Control is dependent on the knowledge of and the ability to detect principle characteristics of the phenomena. Therefore, an experimental study of a 700 delta wing was accomplished to better understand the physical properties of the vortical flow and the vortex breakdownphenomena. Multiple experimental methods were used to characterize the flow field and its influence on the model's surfaces as well as to identify parameters for closed-loop feedback control.
Book Synopsis Controlled Vortical Flow on Delta Wings Through Unsteady Leading Edge Blowing by : National Aeronautics and Space Adm Nasa
Download or read book Controlled Vortical Flow on Delta Wings Through Unsteady Leading Edge Blowing written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-18 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: The vortical flow over a delta wing contributes an important part of the lift - the so called nonlinear lift. Controlling this vortical flow with its favorable influence would enhance aircraft maneuverability at high angle of attack. Several previous studies have shown that control of the vortical flow field is possible through the use of blowing jets. The present experimental research studies vortical flow control by applying a new blowing scheme to the rounded leading edge of a delta wing; this blowing scheme is called Tangential Leading Edge Blowing (TLEB). Vortical flow response both to steady blowing and to unsteady blowing is investigated. It is found that TLEB can redevelop stable, strong vortices even in the post-stall angle of attack regime. Analysis of the steady data shows that the effect of leading edge blowing can be interpreted as an effective change in angle of attack. The examination of the fundamental time scales for vortical flow re-organization after the application of blowing for different initial states of the flow field is studied. Different time scales for flow re-organization are shown to depend upon the effective angle of attack. A faster response time can be achieved at angles of attack beyond stall by a suitable choice of the initial blowing momentum strength. Consequently, TLEB shows the potential of controlling the vortical flow over a wide range of angles of attack; i.e., in both for pre-stall and post-stall conditions. Lee, K. T. and Roberts, Leonard BLOWING; DELTA WINGS; FLOW DISTRIBUTION; LEADING EDGES; VORTICES; AIRCRAFT MANEUVERS; ANGLE OF ATTACK; MOMENTUM; NONLINEARITY; STABILITY...
Book Synopsis An Experimental Investigation of Vortex Breakdown on Slender Delta-wing Planforms by : Alain Pelletier
Download or read book An Experimental Investigation of Vortex Breakdown on Slender Delta-wing Planforms written by Alain Pelletier and published by . This book was released on 1994 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt:
