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Low Speed Investigation Of A Full Span Internal Flow Jet Augmented Flap On A High Wing Model With A 35 Degree Swept Wing Of Aspect Ratio 70
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Book Synopsis Low-speed Investigation of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 35 Degree Swept Wing of Aspect Ratio 7.0 by : Thomas R. Turner
Download or read book Low-speed Investigation of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 35 Degree Swept Wing of Aspect Ratio 7.0 written by Thomas R. Turner and published by . This book was released on 1960 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Investigation of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 35 Degree Swept Wing of Aspect Ratio 7.0 by : Thomas R. Turner
Download or read book Low-speed Investigation of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 35 Degree Swept Wing of Aspect Ratio 7.0 written by Thomas R. Turner and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Speed Investigation of a Full-Span Internal-Flow Jet-Augmented Flap on a High-Wing Model with a 35 Deg Swept Wing of Aspect Ratio 7.0 by :
Download or read book Low-Speed Investigation of a Full-Span Internal-Flow Jet-Augmented Flap on a High-Wing Model with a 35 Deg Swept Wing of Aspect Ratio 7.0 written by and published by . This book was released on 1960 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Investigations of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 30 Degree Swept Wing of Aspect Ratio 7.0 by : Thomas R. Turner
Download or read book Low-speed Investigations of a Full-span Internal-flow Jet-augmented Flap on a High-wing Model with a 30 Degree Swept Wing of Aspect Ratio 7.0 written by Thomas R. Turner and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating by : Marvin P. Fink
Download or read book Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating written by Marvin P. Fink and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
Book Synopsis Investigation of Double Slotted Flaps on a Swept-wing Transport Model by : Rodger L. Naeseth
Download or read book Investigation of Double Slotted Flaps on a Swept-wing Transport Model written by Rodger L. Naeseth and published by . This book was released on 1959 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Speed Wind-Tunnel Investigation of a Reflection Plane Wing Model Equipped with Partial-Span Jet-Augmented Flaps by : JAMES H. JR. OTIS
Download or read book Low-Speed Wind-Tunnel Investigation of a Reflection Plane Wing Model Equipped with Partial-Span Jet-Augmented Flaps written by JAMES H. JR. OTIS and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Langley 300-MPH 7- by 10-foot tunnel with a semispan, rectangular unswept wing of full-span aspect ratio 8.3 and thickness-to-chord ratio of 0.167. Three 50-percent partial-span jet-augmented-flap configurations located inboard, outboard, and at the midsemispan position were tested through a momentum coefficient range from 0 to about 10 and an angle-of-attack range from -10 degrees to approximately 28 degrees. The corresponding flow-field characteristics are presented for a longitudinaltail position of 4 wing chords behind the trailing edge of the wing through a range of tailheight locations of + or - 2 chords. (Author).
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1983 with total page 676 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-wing-fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X (10)6 by : Stanley H. Spooner
Download or read book Low-speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-wing-fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X (10)6 written by Stanley H. Spooner and published by . This book was released on 1951 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed wind-tunnel investigation of a swept-wing model having distributed upper-surface blowing near the wing leading edge or at the flap knee by : William C. Sleeman
Download or read book Low-speed wind-tunnel investigation of a swept-wing model having distributed upper-surface blowing near the wing leading edge or at the flap knee written by William C. Sleeman and published by . This book was released on 1977 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of the Longitudinal Aerodynamic Characteristics of STOL Aircraft with Externally-blown Jet-augmented Flaps by : Marnix F. E. Dillenius
Download or read book Calculation of the Longitudinal Aerodynamic Characteristics of STOL Aircraft with Externally-blown Jet-augmented Flaps written by Marnix F. E. Dillenius and published by . This book was released on 1974 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical investigation was made to develop methods for predicting the longitudinal aerodynamic characteristics of externally-blown, jet-augmented wing-flap combinations. A potential flow analysis was used to develop two models: a wing-flap lifting surface model and a high-bypass-ratio turbofan engine wake model. Use of these two models in sequence provides for calculation of the wing-flap load distribution including the influence of the engine wake. The method can accommodate multiple engines per wing panel and part-span flaps but is limited to the case where the flow and geometry of the configuration are symmetric about a vertical plane containing the wing root chord. Comparisons of predicted and measured lift and pitching moment on unswept and swept wings with one and two engines per panel and with various flap deflection angles indicate satisfactory prediction of lift and moment for flap deflections up to 30 to 40 degrees. At higher flap angles with and without power, the method begins to overpredict lift, due probably to the appearance of flow separation on the flaps.
Book Synopsis Low-speed Investigation of Effects of Wing Leading- and Trailing-edge Flap Deflections and Canard Incidence on a Fighter Configuration Equipped with a Forward-swept Wing by : Thomas G. Gainer
Download or read book Low-speed Investigation of Effects of Wing Leading- and Trailing-edge Flap Deflections and Canard Incidence on a Fighter Configuration Equipped with a Forward-swept Wing written by Thomas G. Gainer and published by . This book was released on 1984 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 by : Leonard M. Rose
Download or read book Low-speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 written by Leonard M. Rose and published by . This book was released on 1948 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-body-tail Configuration in Combination with Leading-edge Devices by : H. Clyde McLemore
Download or read book Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-body-tail Configuration in Combination with Leading-edge Devices written by H. Clyde McLemore and published by . This book was released on 1956 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel to determine the effects on the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. The wing and horizontal tail have an aspect ratio of 3.5, taper ratio of 0.3, leading-edge sweep of 49 degrees, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The trailing-edge air was ejected over highly deflected half- and full-span flaps in combination with several leading-edge-flow control devices including blowing from a slot in the wing leading edge. The momentum coefficient range was investigated was 0 to 0.16 for the trailing-edge blowing and 0 to 0.025 for the leading-edge blowing. Most of the tests were conducted at a Reynolds number of 5,200,000 corresponding to a Mach number of 0.08.
Book Synopsis Flight Investigation of the Low-speed Characteristics of a 450 Swept-wing Fighter-type Airplane with Blowing Boundary-layer Control Applied to the Leading- and Trailing-edge Flaps by : Hervey C. Quigley
Download or read book Flight Investigation of the Low-speed Characteristics of a 450 Swept-wing Fighter-type Airplane with Blowing Boundary-layer Control Applied to the Leading- and Trailing-edge Flaps written by Hervey C. Quigley and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Investigation of Leading-edge and Trailing-edge Flaps on a 47.5 Degree Sweptback Wing of Aspect Ratio 3.4 at a Reynolds Number of 4.4 X (10)6 by : Jerome Pasamanick
Download or read book Low-speed Investigation of Leading-edge and Trailing-edge Flaps on a 47.5 Degree Sweptback Wing of Aspect Ratio 3.4 at a Reynolds Number of 4.4 X (10)6 written by Jerome Pasamanick and published by . This book was released on 1950 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Wind-tunnel Investigation of a Reflection Plane Wing Equipped with Partial-span Jet-augmented Flaps by : James H. Otis
Download or read book Low-speed Wind-tunnel Investigation of a Reflection Plane Wing Equipped with Partial-span Jet-augmented Flaps written by James H. Otis and published by . This book was released on 1961 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
