Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2.30 to 4.62 PDF Download

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Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2.30 to 4.62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2.30 to 4.62 PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

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Book Description

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2.30 to 4.62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2.30 to 4.62 PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

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Book Description

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Deg to 53 Deg at Mach Numbers from 2.30 to 4.62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Deg to 53 Deg at Mach Numbers from 2.30 to 4.62 PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 23

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Book Description

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2. 30 To 4. 62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 Degrees to 53 Degrees at Mach Numbers from 2. 30 To 4. 62 PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722218300
Category :
Languages : en
Pages : 28

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Book Description
Lifting bodies are of interest for possible use as space transportation vehicles because they have the volume required for significant payloads and the aerodynamic capability to negotiate the transition from high angles of attack to lower angles of attack (for cruise flight) and thus safely reenter the atmosphere and perform conventional horizontal landings. Results are presented for an experimental and theoretical study of the aerodynamic characteristics at supersonic speeds for a series of lifting bodies with 75 deg delta planforms, rounded noses, and various upper and lower surface cambers. The camber shapes varied in thickness and in maximum thickness location, and hence in body volume. The experimental results were obtained in the Langley Unitary Plan Wind Tunnel for both the longitudinal and the lateral aerodynamic characteristics. Selected experimental results are compared with calculated results obtained through the use of the Hypersonic Arbitrary-Body Aerodynamic Computer Program. Spearman, M. Leroy and Torres, Abel O. Langley Research Center RTOP 505-69-20-01...

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 to 53 at Mach Numbers from 2.30 to 4.62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -10 to 53 at Mach Numbers from 2.30 to 4.62 PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 23

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Book Description

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -100 to 530 at Mach Numbers from 2.30 to 4.62

Experimental and Theoretical Study of Aerodynamic Characteristics of Some Lifting Bodies at Angles of Attack from -100 to 530 at Mach Numbers from 2.30 to 4.62 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 23

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Book Description

Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies

Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies PDF Author: William Letko
Publisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 22

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Book Description

The Aerodynamic Characteristics of Some Lifting Bodies

The Aerodynamic Characteristics of Some Lifting Bodies PDF Author: David H. Dennis
Publisher:
ISBN:
Category :
Languages : en
Pages : 22

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Book Description

Static Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Blunted Right Triangular Pyramidal Lifting Reentry Configuration for Angles of Attack Up to 110°

Static Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Blunted Right Triangular Pyramidal Lifting Reentry Configuration for Angles of Attack Up to 110° PDF Author: John P. Mugler
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 42

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Book Description

Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0 O to 58 O and Mach Numbers from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0 O to 58 O and Mach Numbers from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 77

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Book Description
An experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a, b axis system was rotated 90°, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.

Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description