Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies PDF Download

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Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies

Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies PDF Author: Thomas L. Fischetti
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 98

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Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies

Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies PDF Author: Thomas L. Fischetti
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 98

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Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45 Degree Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies

Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45 Degree Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies PDF Author: Thomas L. Fischetti
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94

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Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations

Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 82

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Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.

A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance

A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance PDF Author: Donald L. Loving
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92

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Book Description

Basic Pressure Measurements at a Mach Number of 1/43 on a Thing 45 Degree Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations

Basic Pressure Measurements at a Mach Number of 1/43 on a Thing 45 Degree Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations PDF Author: John P. Jr Mugler
Publisher:
ISBN:
Category : Wall pressure (Aerodynamics)
Languages : en
Pages : 78

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Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.

Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low-aspect-ratio Delta Wing in Combination with Basic and Indented Bodies

Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low-aspect-ratio Delta Wing in Combination with Basic and Indented Bodies PDF Author: John P. Mugler
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 79

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Book Description
Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.

The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0

The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 PDF Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24

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Book Description
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.

Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7

Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 PDF Author: Marvin Kussoy
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32

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Book Description

Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number

Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number PDF Author: George H. Holdaway
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 62

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Book Description

Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms

Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms PDF Author: George H. Holdaway
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82

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Book Description