High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF Download

Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF full book. Access full book title High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase by Marvin P. Fink. Download full books in PDF and EPUB format.

High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase

High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF Author: Marvin P. Fink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40

Get Book Here

Book Description

High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase

High-pressure Blowing Over Flap and Wing Leading Edge of a Large-scale 49 Degrees Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF Author: Marvin P. Fink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40

Get Book Here

Book Description

High-pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-scale 49 Degree Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase

High-pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-scale 49 Degree Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF Author: Marvin P. Fink
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 40

Get Book Here

Book Description
A 49 degree swept-wing complete model equipped for high-pressure blowing full span at two chordwise locations at the leading edge of a full-span wing and over a half-span flap has been tested in the Langley full-scale tunnel to determine the effectiveness of blowing at the leading edge as a supplementary leading-edge stall control at high lift coefficients.

High-pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-scale 49° Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase

High-pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-scale 49° Swept Wing-body-tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase PDF Author: Marvin P. Fink
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 40

Get Book Here

Book Description

Surface Pressure Distributions on a Large-scale 49© Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge

Surface Pressure Distributions on a Large-scale 49© Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge PDF Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 134

Get Book Here

Book Description

Surface Pressure Distributions on a Large-scale 49 Degree Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge

Surface Pressure Distributions on a Large-scale 49 Degree Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge PDF Author: H. Clyde McLemore
Publisher:
ISBN:
Category :
Languages : en
Pages : 128

Get Book Here

Book Description

Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-body-tail Configuration in Combination with Leading-edge Devices

Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-body-tail Configuration in Combination with Leading-edge Devices PDF Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 57

Get Book Here

Book Description
An investigation has been conducted in the Langley full-scale tunnel to determine the effects on the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. The wing and horizontal tail have an aspect ratio of 3.5, taper ratio of 0.3, leading-edge sweep of 49 degrees, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The trailing-edge air was ejected over highly deflected half- and full-span flaps in combination with several leading-edge-flow control devices including blowing from a slot in the wing leading edge. The momentum coefficient range was investigated was 0 to 0.16 for the trailing-edge blowing and 0 to 0.025 for the leading-edge blowing. Most of the tests were conducted at a Reynolds number of 5,200,000 corresponding to a Mach number of 0.08.

Aerodynamic Characteristics in Sideslip of a Large-scale 49 Degree Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge

Aerodynamic Characteristics in Sideslip of a Large-scale 49 Degree Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge PDF Author: H. Clyde McLemore
Publisher:
ISBN:
Category :
Languages : en
Pages : 46

Get Book Here

Book Description

Aerodynamic Characteristics of a Large-Scale Unswept Wing-Body-Tail Configuration with Blowing Applied Over the Flap and Wind Leading Edge

Aerodynamic Characteristics of a Large-Scale Unswept Wing-Body-Tail Configuration with Blowing Applied Over the Flap and Wind Leading Edge PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 228

Get Book Here

Book Description

Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps

Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps PDF Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 72

Get Book Here

Book Description

Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating

Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating PDF Author: Marvin P. Fink
Publisher:
ISBN:
Category : Compressed air
Languages : en
Pages : 52

Get Book Here

Book Description
An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.