Download or read book The Aerodynamics of Inverted Leading Edge Flaps on Delta Wings written by 3 J.F. Marchman and published by . This book was released on 1981 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamics of a Delta Wing with Leading Edge Vortex Flaps written by Daniel Francis Hunter and published by . This book was released on 1986 with total page 428 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Analytical Observations on the Aerodynamics of a Delta Wing with Leading Edge Flaps written by Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics and published by . This book was released on 1986 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Performance of 60deg Delta Wings written by B. K. Hu and published by . This book was released on 1989 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Leading and Trailing edge Flaps on Clipped Delta Wings with and Without Wing Camber at Supersonic Speeds written by Gloria Hernandez and published by . This book was released on 1994 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Effects of an Inverse taper Leading edge Flap on the Aerodynamic Loading Characteristics of a 45 Sweptback Wing at Mach Numbers to 0 90 written by Fred A. Demele and published by . This book was released on 1959 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical Studies on Flapped Delta Wings written by Sejong Oh and published by . This book was released on 1988 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Influence of Airfoil Geometry on Delta Wing Leading edge Vortices and Vortex induced Aerodynamics at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1992 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2 0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Leading edge Flap Performance on Delta and Double delta Wings at Supersonic Speeds written by Peter F. Covell and published by . This book was released on 1987 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical Studies on Flapped Delta Wings written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of leading edge flaps on the aerodynamic characteristics of a low aspect-ratio delta wing are studied theoretically. As an extension of the classical crossflow plane analysis and in order to include separated shear layers, an analogy between three dimensional steady conical and two dimensional unsteady self-similar flows is explored. This analogy provides a simple steady-unsteady relationship. The criteria for the validity of the steady-unsteady analogy are also examined. Two different theoretical techniques are used to represent the separated shear layers based on the steady-unsteady analogy, neglecting the trailing edge effect. In the first approach, each vortex system is represented by a pair of concentrated vortices connected to the separation points by straight feeding sheets. In the second approach, the vortex cloud method is adopted for simulating the flow field in the crossflow plane. The separated shear layers are replaced with a cloud of discrete vortices and the boundary element method is employed to represent the wing trace by a vorticity distribution. A simple merging scheme is used to model the core region of the vortical flow as a single vortex by imposing a restriction on the shear layer rotation angle. The results are compared with experiments and with results from 3-D panel calculations. Oh, S. and Tavella, D. and Roberts, L. Unspecified Center AERODYNAMIC CHARACTERISTICS; BOUNDARY VALUE PROBLEMS; DELTA WINGS; LEADING EDGE FLAPS; MATHEMATICAL MODELS; VORTICES; BOUNDARY ELEMENT METHOD; FLOW DISTRIBUTION; LOW ASPECT RATIO; SHEAR LAYERS...

Download or read book Effect of Leading And Trailing Edge Flaps on Clipped Delta Wings with and Without Wing Camber at Supersonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the aerodynamic characteristics of thin, moderately swept fighter wings has been conducted to evaluate the effect of camber and twist on the effectiveness of leading- and trailing-edge flaps at supersonic speeds in the Langley Unitary Plan Wind Tunnel. The study geometry consisted of a generic fuselage with camber typical of advanced fighter designs without inlets, canopy, or vertical tail. The model was tested with two wing configurations an uncambered (flat) wing and a cambered and twisted wing. Each wing had an identical clipped delta planform with an inboard leading edge swept back 65 deg and an outboard leading edge swept back 50 deg. The trailing edge was swept forward 25 deg. The leading-edge flaps were deflected 4 deg to 15 deg, and the trailing-edge flaps were deflected from -30 deg to 10 deg. Longitudinal force and moment data were obtained at Mach numbers of 1.60, 1.80, 2.00, and 2.16 for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.16 x 10(exp 6) per foot and for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.0 x 10(exp 6) per foot. Vapor screen, tuft, and oil flow visualization data are also included. Hernandez, Gloria and Wood, Richard M. and Covell, Peter F. Langley Research Center RESEARCH; INVESTIGATION; DESIGN; EXPLORATION...

Download or read book Comparison of Longitudinal Aerodynamic Characteristics of Curved and Straight Leading edge Delta Wings at Mach Numbers 3 and 6 written by Dewey E. Wornom and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Performance of 600 Delta Wings written by B. K. Hu and published by . This book was released on 1990 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low Speed Aerodynamic Characteristics of 60 Rounded Leading edge Delta Wing with Vortex Flaps written by Kenichi Rinoie and published by . This book was released on 1996 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low Speed Aerodynamic Characteristics of 60 Degree Rounded Leading edge Delta Wing with Vortex Flaps Part 1 written by Kenichi Rinoie and published by . This book was released on 1996 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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. " --