Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30° and 45° Swept Wings PDF Download

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Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30° and 45° Swept Wings

Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30° and 45° Swept Wings PDF Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 58

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Book Description

Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30° and 45° Swept Wings

Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30° and 45° Swept Wings PDF Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 58

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Book Description

Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30 Deg and 45 Deg Swept Wings

Investigation at Transonic Speeds to Determine Lateral Control Effectiveness of Blowing Laterally Over Surfaces of 30 Deg and 45 Deg Swept Wings PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 62

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Book Description

Lateral-control Investigation at Transonic Speeds of Differentially Deflected Horizontal-tail Surfaces for a Configuration Having a 6-percent-thick 45 Degrees Sweptback Wing

Lateral-control Investigation at Transonic Speeds of Differentially Deflected Horizontal-tail Surfaces for a Configuration Having a 6-percent-thick 45 Degrees Sweptback Wing PDF Author: Chris C. Critzos
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Lateral-control Investigation at Transonic Speeds of Differentially Deflected Horizontal-tail Surfaces for a Configuration Having a 6 Percent-thick 45 Degree Sweptback Wing

Lateral-control Investigation at Transonic Speeds of Differentially Deflected Horizontal-tail Surfaces for a Configuration Having a 6 Percent-thick 45 Degree Sweptback Wing PDF Author: Chris C. Critzos
Publisher:
ISBN:
Category :
Languages : en
Pages : 34

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Book Description

Patent Law Revision

Patent Law Revision PDF Author: United States. Congress. Senate. Committee on the Judiciary
Publisher:
ISBN:
Category : Patent laws and legislation
Languages : en
Pages : 66

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Book Description

Index Aeronauticus

Index Aeronauticus PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 806

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Book Description

Preliminary Investigation of Spoiler Lateral Control on a 42 Degree Sweptback Wing at Transonic Speeds

Preliminary Investigation of Spoiler Lateral Control on a 42 Degree Sweptback Wing at Transonic Speeds PDF Author: Leslie E. Schneiter
Publisher:
ISBN:
Category :
Languages : en
Pages : 14

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Book Description

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

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 PDF Author: Raymond D. Vogler
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 22

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Book Description
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.

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

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 PDF Author: JACK F. RUNCKEL
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

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Book Description
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).

Force Tests Results for Body-mounted Lateral Controls and Speed Brakes on a 45 Degree Swept-wing Model at Mach Numbers from 0.80 to 0.98

Force Tests Results for Body-mounted Lateral Controls and Speed Brakes on a 45 Degree Swept-wing Model at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32

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Book Description
An investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic characteristics of several body-mounted lateral-control and speed-brake configurations. The basic model had a 45 degree swept wing with an aspect ratio of 3. Six-component balance data were obtained at Mach numbers of 0.80, 0.94, and 0.98 for angles of attack that usually ranged from about zero to 21 degrees.