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Investigation Of Pressure Distribution Over An Extended Leading Edge Flap On A 42 Degree Sweptback Wing
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Book Synopsis Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing by :
Download or read book Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing written by and published by . This book was released on 1947 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Book Synopsis Pressure-distribution Measurements Over an Extensible Leading-edge Flap on Two Wings Having Leading-edge Sweep of 42 Degree and 52 Degree by : Reino J. Salmi
Download or read book Pressure-distribution Measurements Over an Extensible Leading-edge Flap on Two Wings Having Leading-edge Sweep of 42 Degree and 52 Degree written by Reino J. Salmi and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 by : Harold Mirels
Download or read book Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 written by Harold Mirels and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Book Synopsis Air Load Distributions on a Flapped Wing Resulting from Leading-edge and Trailing-edge Blowing by : H. Clyde McLemore
Download or read book Air Load Distributions on a Flapped Wing Resulting from Leading-edge and Trailing-edge Blowing written by H. Clyde McLemore and published by . This book was released on 1957 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of recent wind-tunnel pressure-distribution tests on a large-scale boundary-layer-control model with a 49 degree sweptback wing have indicated that blowing air at low blowing rates over highly deflected trailing-edge flaps does not produce any unusual flap-load or wing-load problems at low speed. Blowing at very high momentum rates, however, produces large increased in flap loads and extremely high local negative pressures over the flap leading edge.
Book Synopsis Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps by : Roy H. Lange
Download or read book Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps written by Roy H. Lange and published by . This book was released on 1949 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions Over a Retracted Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers Up to 0.9 by : Jones F. Cahill
Download or read book Pressure Distributions Over a Retracted Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers Up to 0.9 written by Jones F. Cahill and published by . This book was released on 1951 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions over a retracted leading-edge slat on a 40 degree sweptback wing are presented for a series of angles of attack up to maximum lift at Mach numbers of 0.1, 0.4, 0.6, 0.7, 0.8, 0.85, and 0.9. These data were obtained in the Langley low-turbulence pressure tunnel at a constant Reynolds number of approximately 3,000,000. The Reynolds number was maintained approximately constant through the Mach number range by varying the stagnation pressure.
Book Synopsis Pressure Distributions from Subsonic Tests of an Advanced Laminar-flow-control Wing with Leading- and Trailing-edge Flaps by : Zachary T. Applin
Download or read book Pressure Distributions from Subsonic Tests of an Advanced Laminar-flow-control Wing with Leading- and Trailing-edge Flaps written by Zachary T. Applin and published by . This book was released on 1988 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1970 with total page 772 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1985 with total page 1152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of Several Factors Affecting the Stability Contributed by a Horizontal Tail at Various Vertical Positions on a Sweptback-wing Airplane Model by : Gerald V. Foster
Download or read book A Study of Several Factors Affecting the Stability Contributed by a Horizontal Tail at Various Vertical Positions on a Sweptback-wing Airplane Model written by Gerald V. Foster and published by . This book was released on 1956 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was made in the Langley 19-foot pressure tunnel to determine the effects of fuselage afterbody shape, split flaps, end variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail.,to an airplane with the wing leading edge swept back 42 degrees . Supplementary tests were made to determine some of the characteristics of the air flow In the vicinity of the tail, the wing being equipped with 0.575-span leading-edge flaps and 0.5-spanpsn split flaps. All data were obtained at a Reynolds number of 6,800,000.
Book Synopsis Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 by : P. Calvin Stainback
Download or read book Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 written by P. Calvin Stainback and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics Publisher : ISBN 13 : Total Pages :48 pages Book Rating :4.F/5 ( download)
Book Synopsis Experimental Studies of a Delta Wing with Leading Edge Flaps by : Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics
Download or read book Experimental Studies 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 1987 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1978 with total page 258 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing with Symmetrical Circular-arc Section and 30-percent-chord Trailing-edge Flap by : K. R. Czarnecki
Download or read book Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing with Symmetrical Circular-arc Section and 30-percent-chord Trailing-edge Flap written by K. R. Czarnecki and published by . This book was released on 1950 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc liquid-film flow studies have also been made. Results obtained at a Mach number of 1.62 and a Reynolds number range of 550,000 to1,070,000 indicate good agreement between theoretical and experimental pressure distributions except on the low-pressure side of the flap near the trailing edge and on the high-pressure side of the flap and wing near the hinge line. In these regions, laminar separation occurred. As a result of the flow separations, the experimental increments in aerodynamic coefficients due to angle of attack or flap deflection were generally smaller and the slopes of the experimental curves lower than the theoretical coefficient increments and slopes. The experimental section-coefficient curves also exhibit a break or shift that may result in undesirable stability and control characteristics such as snaking and nonlinear stick force-deflection relationships.
Book Synopsis Flight Investigation of the Low-Speed Characteristics of a 45 Deg Swept-Wing Fighter-Type Airplane with Blowing Boundary-Layer Control Applied to the Leading- and Trailing-Edge Flaps by :
Download or read book Flight Investigation of the Low-Speed Characteristics of a 45 Deg Swept-Wing Fighter-Type Airplane with Blowing Boundary-Layer Control Applied to the Leading- and Trailing-Edge Flaps written by and published by . This book was released on 1960 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
