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Wind Tunnel Investigation At Low Speed Of A Twisted And Cambered Wing Swept Back 63 Degrees With Vortex Generators And Fences
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Book Synopsis Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences by : James A. Weilberg
Download or read book Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences written by James A. Weilberg and published by . This book was released on 1952 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing by : Arvid L. Keith
Download or read book Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing written by Arvid L. Keith and published by . This book was released on 1950 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
Book Synopsis Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 by : Earl D. Knechtel
Download or read book Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 written by Earl D. Knechtel and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Book Synopsis Wind-tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45° Sweptback Semispan Wing of Aspect Ratio 1.59 Equipped with Various 25-percent-chord Plain Ailerons by : Harold S. Johnson
Download or read book Wind-tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45° Sweptback Semispan Wing of Aspect Ratio 1.59 Equipped with Various 25-percent-chord Plain Ailerons written by Harold S. Johnson and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at low speed was made to determine the lateral control characteristics of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain unsealed ailerons. Variations of the lateral-control data with aileron span and spanwise location were determined through a large aileron-deflection range for various angles of attack up to about the angle of maximum lift.
Book Synopsis Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls by : Robert E. Dannenberg
Download or read book Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls written by Robert E. Dannenberg and published by . This book was released on 1950 with total page 678 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
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 Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing by : Arvid L. Keith
Download or read book Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing written by Arvid L. Keith and published by . This book was released on 1955 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Book Synopsis Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings by : Macon C. Ellis
Download or read book Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings written by Macon C. Ellis and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
Book Synopsis Flutter Investigation at Low Speed of a 40 Degree Sweptback Wing with Pylon-mounted Stores, Tested as a Semispan-cantilever Wing and as a Full-span Wing on a Towed Airplane Model by : Albert P. Martina
Download or read book Flutter Investigation at Low Speed of a 40 Degree Sweptback Wing with Pylon-mounted Stores, Tested as a Semispan-cantilever Wing and as a Full-span Wing on a Towed Airplane Model written by Albert P. Martina and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel flutter investigations at Mach numbers up to 0.30 have been conducted on a 40 degree sweptback wing having pylon-mounted stores located at 73.5 percent of the semispan. The investigations were conducted on a semispan-cantilever wing with root fixed and with the full-span wing mounted on an autopilot-controlled model of a fighter-type airplane flown on the end of a towline. The store loadings were varied from 55 to 88 percent of the wing-panel weight, and the store pitch inertias were varied from 66 to 181 percent of the wing-panel pitch inertia. Most of the data were obtained with the store centers of gravity located at 15 percent of the local wing chord.
Book Synopsis Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel by : Rodger L. Naeseth
Download or read book Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel written by Rodger L. Naeseth and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
Book Synopsis Effects of Canopy Shape on Low-speed Aerodynamic Characteristics of a 550 Swept Parawing with Large-diameter Leading Edges by : Delwin R. Croom
Download or read book Effects of Canopy Shape on Low-speed Aerodynamic Characteristics of a 550 Swept Parawing with Large-diameter Leading Edges written by Delwin R. Croom and published by . This book was released on 1964 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed wind-tunnel investigation was conducted to study effects of wing-canopy shape on the aerodynamic characteristics and spreader-bar load of a 550 swept parawing having large-diameter leading edges and keel. The canopy-flat-pattern sweep angles investigated on the 550 swept wing were 42.50, 450, 47.50, 500, and 52.50. Several other modifications to the canopy shape were also studied, such as removal of single, double, and compound gores from the rear part of each canopy lobe. A study of the effects of wing-leading-edge sweep angle was made between sweep angles of 500 and 600 and effects of leading-edge diameter were obtained at the basic 550 sweep angle. Effects of keel web height were determined for a constant trailing-edge length and also for trailing-edge lengths that varied with web height.
