Transonic Wind-tunnel Investigation of the Interference Between a 45© Sweptback Wing and a Systematic Series of Four Bodies PDF Download
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Author: Donald L. Loving
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
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Book Description
Author: Donald L. Loving
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
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Book Description
Author: Melvin M. Carmel
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 50
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Book Description
Author: Thomas C. Kelly
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 82
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Book Description
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Author: Robert J. Platt
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50
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Book Description
A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
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Book Description
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.
Author: B. H. Goethert
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 420
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Book Description
Numerous aspects of transonic aerodynamics include wall interference corrections in conventional wind tunnels, subsonic flow in a variety of wind tunnels, and test results from transonic wind tunnels. 1961 edition.
Author: Louis W. Habel
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 30
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Book Description
Author: Jack F. Runckel
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 104
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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 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.
Author: J. W. Usry
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44
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Book Description
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 65
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Book Description
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.
