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Lateral Control Investigation Of Flap Type Controls On A Wing With Quarter Chord Line Swept Back 60 Degrees Aspect Ratio 4 Taper Ratio 06 And Naca 65a006 Airfoil Section
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Book Synopsis Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Raymond D. Vogler
Download or read book Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Raymond D. Vogler and published by . This book was released on 1950 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA search program, an investigation by the transonic-bump method through a Mach range of 0.7 to 1.15 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Book Synopsis Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Raymond D. Vogler
Download or read book Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Raymond D. Vogler and published by . This book was released on 1949 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA research program, an investigation by the transonic-bump method through a Mach range of 0.6 to 1.2 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of 30-percent-chord flap-type controls of various spans. The wing of the semispan fuselage-wing combination had 45 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Book Synopsis Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Robert F. Thompson
Download or read book Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Robert F. Thompson and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
Book Synopsis Lateral-control Investigation of Flat-type Controls on a Wing Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Robert F. Thomson
Download or read book Lateral-control Investigation of Flat-type Controls on a Wing Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Robert F. Thomson and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lateral-control Investigation of Flap-type Controls on a Wing with Unswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Alexander D. Hammond
Download or read book Lateral-control Investigation of Flap-type Controls on a Wing with Unswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Alexander D. Hammond and published by . This book was released on 1950 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lateral-control Investigation of Flap-type and Spoiler-type Controls on a Wing with Quarter-chord-line Sweepback of 60 Degrees, Aspect Ratio 2, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Alexander D. Hammond
Download or read book Lateral-control Investigation of Flap-type and Spoiler-type Controls on a Wing with Quarter-chord-line Sweepback of 60 Degrees, Aspect Ratio 2, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Alexander D. Hammond and published by . This book was released on 1950 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: As a part of an NACA research program, an investigation by the transonic-bump method through a Mach number range of 0.6 to 1.15 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of a semispan wing-fuselage combination equipped with flap-type and spoiler-type controls.
Book Synopsis Lateral-control Investigation of Flap-type Controls on a Wing with Upswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Alexander D. Hammond
Download or read book Lateral-control Investigation of Flap-type Controls on a Wing with Upswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Alexander D. Hammond and published by . This book was released on 1950 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA research program, an investigation by the transonic-bump method through a Mach range of 0.7 to 1.15 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls having various spans and spanwise locations. The wing of the semispan fuselage-wing combination had an unswept quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Book Synopsis USAF Stability and Control Datcom by : Douglas Aircraft Company
Download or read book USAF Stability and Control Datcom written by Douglas Aircraft Company and published by . This book was released on 1975 with total page 642 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Low-speed Investigation of a High-lift Lateral-control Device Consisting of a Spoiler-slot-deflector and a Trailing-edge Flap on a Tapered 45 Degree Sweptback Wing by : Alexander D. Hammond
Download or read book A Low-speed Investigation of a High-lift Lateral-control Device Consisting of a Spoiler-slot-deflector and a Trailing-edge Flap on a Tapered 45 Degree Sweptback Wing written by Alexander D. Hammond and published by . This book was released on 1956 with total page 21 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 spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap extending from the 14- to the 67-percent-semispan station. The wing has a sweepback of 45 degree of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil parallel to the plane of symmetry. Additional tests were made with the flap neutral to evaluate the effects of deflector projection on the characteristics of the wing equipped with a spoiler-slot-deflector configuration having the same span and spanwise position as the spoiler and deflector had with the flap deflected.
Book Synopsis Lateral Control Characteristics of Two Structural Similar Flexible Wings with 45 Degrees Sweep: a Sweptback Wing and a Wing with M Plan Form by : Rodger L. Naeseth
Download or read book Lateral Control Characteristics of Two Structural Similar Flexible Wings with 45 Degrees Sweep: a Sweptback Wing and a Wing with M Plan Form written by Rodger L. Naeseth and published by . This book was released on 1954 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed wind-tunnel investigation was made to determine the static lateral control characteristics of flap-type and retractable spoiler-type ailerons on a rigid sweptback wing, a flexible sweptback wing, and a flexible M-wing. A few tests were also made with a half-delta tip control on the flexible sweptback wing. The semispan wing models were of aspect ratio 6.0, taper ratio of 0.6, and had NACA 65A009 airfoil sections parallel to the free-stream direction. The quarter-chord lines of the wings were swept 45 degrees and the break in the M-wing was at the half semispan location.
Book Synopsis Lateral-control Investigation on a 37 Degrees Sweptback Wing of Aspect Ratio 6 at a Reynolds Number of 6,800,000 by : Robert R. Graham
Download or read book Lateral-control Investigation on a 37 Degrees Sweptback Wing of Aspect Ratio 6 at a Reynolds Number of 6,800,000 written by Robert R. Graham and published by . This book was released on 1949 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30 Deg and 45 Deg Swept Wings by :
Download or read book Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30 Deg and 45 Deg Swept Wings written by and published by . This book was released on 1959 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of the Lateral Controllability with Flap and Plug Ailerons on a Sweptback-wing Model Having Full-span Flaps by : Powell M. Lovell
Download or read book A Comparison of the Lateral Controllability with Flap and Plug Ailerons on a Sweptback-wing Model Having Full-span Flaps written by Powell M. Lovell and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight-tunnel investigation has been made to compare the dynamic lateral control characteristics provided by step plug ailerons on a sweptback-wing model having full-span flaps. The model had a 38 degree sweptback wing with an aspect ratio of 3 and a taper ratio of 0.05. The static stability and control characteristics of the flight-test model were determined from force tests and the time-lag characteristics of the ailerons were determined from stand tests in which there was freedom only in roll. Flight tests of the model were made over a range of lift coefficient from 1.0 through the stall.
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 1961 with total page 1 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 was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
Book Synopsis Lateral-control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge by : Robert R. Graham
Download or read book Lateral-control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge written by Robert R. Graham and published by . This book was released on 1950 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
