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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
Download 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 full books in PDF, epub, and Kindle. Read online 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 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 Wind-tunnel Investigation of a Large 35 ̊swept-wing Jet Transport Model with an External-flow Jet-augmented Double-slotted Flap by : Kiyoshi Aoyagi
Download or read book Wind-tunnel Investigation of a Large 35 ̊swept-wing Jet Transport Model with an External-flow Jet-augmented Double-slotted Flap written by Kiyoshi Aoyagi and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests of swept wing jet transport aircraft model with four pod mounted engines under wing and external flow, jet augmented double slotted flap.
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 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 Aerodynamic Characteristics of a Large-scale Semispan Model with a Swept Wing and an Augmented Jet Flap with Hypermixing Nozzles by :
Download or read book Aerodynamic Characteristics of a Large-scale Semispan Model with a Swept Wing and an Augmented Jet Flap with Hypermixing Nozzles written by and published by . This book was released on 1979 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Wind-tunnel Investigation of a Semispan STOL Jet Transport Wing with Deflected Thrust and Blowing Boundary-layer Control by : Robert L. Henderson
Download or read book Low-speed Wind-tunnel Investigation of a Semispan STOL Jet Transport Wing with Deflected Thrust and Blowing Boundary-layer Control written by Robert L. Henderson and published by . This book was released on 1971 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the static longitudinal aerodynamic characteristics of a semispan swept wing with an aspect ratio of 3.92 and having deflected thrust and blowing boundary-layer control was performed mainly in a low-speed tunnel with a 3.7-m (12-ft) octagonal test section at the Langley Research Center. Thrust was provided by two pod-mounted ducted fans equipped with 60' exhaust deflection vanes, and boundary-layer control was provided by air blowing through a slot over a full-span plain trailing-edge flap.
Book Synopsis Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 by : Kenneth P. Spreemann
Download or read book Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Book Synopsis Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap by : Jerry V. Kirk
Download or read book Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap written by Jerry V. Kirk and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections by : Jack F. Runckel
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections written by Jack F. Runckel and published by . This book was released on 1956 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Book Synopsis Low Speed Aerodynamic Characteristics of a Large Scale STOL Transport Model with an Augmented Jet Flap by :
Download or read book Low Speed Aerodynamic Characteristics of a Large Scale STOL Transport Model with an Augmented Jet Flap written by and published by . This book was released on 1971 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Beyond Tube-and-Wing by : Bruce Larrimer
Download or read book Beyond Tube-and-Wing written by Bruce Larrimer and published by . This book was released on 2020-06-15 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of a Four-engine Externally Blowing Jet-flap STOL Airplane Model by : Raymond D. Vogler
Download or read book Wind-tunnel Investigation of a Four-engine Externally Blowing Jet-flap STOL Airplane Model written by Raymond D. Vogler and published by . This book was released on 1970 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Determination of low speed longitudinal aerodynamic characteristics of four engine externally blowing jet-flap STOL aircraft
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 Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by : Charles F. Whitcomb
Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Book Synopsis Low-speed Static Wind-tunnel Investigation of a Half-span Fuselage and Variable-sweep Pressure Wing Model by : John E. Lamar
Download or read book Low-speed Static Wind-tunnel Investigation of a Half-span Fuselage and Variable-sweep Pressure Wing Model written by John E. Lamar and published by . This book was released on 1971 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: The experimental balance and pressure data obtained from tests of an untwisted variable-sweep wing with an outboard pivot exhibited nonlinearities in both total normalforce-coefficient and pitching-moment-coefficient curves for all sweep angles and fuselage conditions. These total effects have been traced back through the section data and pressure distributions to find the causes. The causes of these nonlinearities were found to be (1) separation of flow on the outer panel and (2) a leading-edge vortex flow on the inner panel. A fuselage added to the wing had little effect on the aerodynamic characteristics. Predictions of wing loadings and performance characteristics were made by using the modified Multhopp method and a comparison with experimental results indicated reasonable agreement. The changes in span loading as a result of leading-edge shed-vortex formation and flow separation at the higher angles of attack caused an increase in the induced-drag parameter.
