Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0 PDF Download

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Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0

Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0 PDF Author: Paul C. Simon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 46

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Book Description

Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0

Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0 PDF Author: Paul C. Simon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 46

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Book Description

Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79

Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 PDF Author: Owen H. Davis
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34

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Book Description

Performance Summary and Analysis of a Mach 3.0 Design Axisymmetric All-external-compression Double-cone Inlet Mach Number Range 3.0 to 0.8

Performance Summary and Analysis of a Mach 3.0 Design Axisymmetric All-external-compression Double-cone Inlet Mach Number Range 3.0 to 0.8 PDF Author: John L. Allen
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24

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Book Description

PERFORMANCE SUMMARY AND ANALYSIS OF A MACH 3.0 DESIGN AXISYMMETRIC ALL-EXTERNAL-COMPRESSION DOUBLE-CONE INLET FROM MACH NUMBER 3.0 TO 0.8

PERFORMANCE SUMMARY AND ANALYSIS OF A MACH 3.0 DESIGN AXISYMMETRIC ALL-EXTERNAL-COMPRESSION DOUBLE-CONE INLET FROM MACH NUMBER 3.0 TO 0.8 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 20

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Book Description

Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in Mach Number Range 2.07 to 1.48

Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in Mach Number Range 2.07 to 1.48 PDF Author: John L. Allen
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36

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Book Description

Performance of a Mach 3.0 External-internal- Compression Axisymmetric Inlet at Mach Numbers from 2.0 to 3.5

Performance of a Mach 3.0 External-internal- Compression Axisymmetric Inlet at Mach Numbers from 2.0 to 3.5 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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Book Description

Performance Summary and Analysis of a Mach 3.0 Design Axisymmetric All External Compression Double Cone Inlet Form Mach Number 3.0 - 0.8

Performance Summary and Analysis of a Mach 3.0 Design Axisymmetric All External Compression Double Cone Inlet Form Mach Number 3.0 - 0.8 PDF Author: John L. Allen
Publisher:
ISBN:
Category :
Languages : en
Pages : 16

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Book Description

Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5

Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5 PDF Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252

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Book Description

A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14°

A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14° PDF Author: Leroy L. Presley
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 58

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Book Description

Performance of External-internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0

Performance of External-internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0 PDF Author: Leonard J. Obery
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 21

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Book Description
An inlet with combined external and internal compression, formed by spike and cowl oblique shocks, and an over-all length of 2.5 inlet diameters was investigated at Mach numbers from 3.0 to 2.0 over a range of angles of attack. At the design Mach number of 3.0 the low angle cowl, which turned the flow supersonically, generated two internal shocks and focused them on the centerbody surface. These compression waves, with their high pressure gradient, were cancelled by abrupt centerbody turning. This investigation showed that with proper boundary-layer control on the centerbody this method of internal compression did not adversely affect the high performance of the inlet.