The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90 PDF Download

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The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90 PDF Author: Fred A. Demele
Publisher:
ISBN:
Category :
Languages : en
Pages : 112

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The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90 PDF Author: Fred A. Demele
Publisher:
ISBN:
Category :
Languages : en
Pages : 112

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Book Description

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading of a 45 Degree Sweptback Wing at Mach Numbers to 0.90

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading of a 45 Degree Sweptback Wing at Mach Numbers to 0.90 PDF Author: Fred A. Demele
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 108

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The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92 PDF Author: Fred A. Demele
Publisher:
ISBN:
Category :
Languages : en
Pages : 57

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Book Description

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 Degrees of Sweepback at Mach Numbers to 0.92

The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 Degrees of Sweepback at Mach Numbers to 0.92 PDF Author: Fred A. Demele
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 57

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Book Description
An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of 3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16 degrees.

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

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 PDF Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 644

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Book Description
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.

Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers of 0.40 to 0.93 of a 45© Sweptback Wing of Aspect Ratio 4

Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers of 0.40 to 0.93 of a 45© Sweptback Wing of Aspect Ratio 4 PDF Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56

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Book Description

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1364

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Monthly Catalog of United States Government Publications, Cumulative Index

Monthly Catalog of United States Government Publications, Cumulative Index PDF Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1366

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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 : 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.

Aerodynamic Loading Characteristics in Sideslip of a 45© Sweptback Wing with and Without a Fence at High Subsonic Speeds

Aerodynamic Loading Characteristics in Sideslip of a 45© Sweptback Wing with and Without a Fence at High Subsonic Speeds PDF Author: Richard E. Kuhn
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50

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Book Description