Author: John T. Sinnette
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 74
Book Description
The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested.
Performance of NACA Eight-stage Axial-flow Compressor Designed on the Basis of Airfoil Theory
Author: John T. Sinnette
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 74
Book Description
The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 74
Book Description
The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested.
Performance of NACA Eight-stage Axial-flow Compressor at Simulated Altitude
Author: J. Austin King
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 30
Book Description
An investigation has been conducted by the NACA to determine the design-performance characteristics of the NACA eight-stage axial-flow compressor and the effect of altitude on the performance. The compressor was tested at simulated altitudes of 50,000; 36,000; and 27,000 feet at rotor speeds corresponding to compressor Mach numbers of 0.80, 0.85, 0.90, and 0.95 wit varying air flow at each speed.
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 30
Book Description
An investigation has been conducted by the NACA to determine the design-performance characteristics of the NACA eight-stage axial-flow compressor and the effect of altitude on the performance. The compressor was tested at simulated altitudes of 50,000; 36,000; and 27,000 feet at rotor speeds corresponding to compressor Mach numbers of 0.80, 0.85, 0.90, and 0.95 wit varying air flow at each speed.
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
Book Description
Wartime Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 334
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 334
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Charts of Pressure Rise Obtainable with Airfoil-type Axial-flow Cooling Fans
Author: A. Kahane
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 578
Book Description
Charts are presented to show the pressure rise that is obtainable in an engine-cooling installation with a typical airfoil-type propeller-speed fan. The charts cover fans of the stator-rotor, rotor-stator, and rotor alone configurations, with blades incorporating both the highly cambered 65-series blower-blade sections and the conventional low-cambered airfoil sections. The effects of operation of a geared fan with rotational speeds limited by compressibility considerations and the effects of initial rotational inflow are indicated. Use of the charts to predict the pressure rise obtainable with any fan of the types considered is illustrated in a sample calculation.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 578
Book Description
Charts are presented to show the pressure rise that is obtainable in an engine-cooling installation with a typical airfoil-type propeller-speed fan. The charts cover fans of the stator-rotor, rotor-stator, and rotor alone configurations, with blades incorporating both the highly cambered 65-series blower-blade sections and the conventional low-cambered airfoil sections. The effects of operation of a geared fan with rotational speeds limited by compressibility considerations and the effects of initial rotational inflow are indicated. Use of the charts to predict the pressure rise obtainable with any fan of the types considered is illustrated in a sample calculation.
Investigation of an Impulse Axial-flow Compressor
Author: John R. Erwin
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 56
Book Description
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 56
Book Description
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 876
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 876
Book Description
Material Presented at the Conference on Compressor Research at Aircraft Engine Research Laboratory on September 11, 1946
Author:
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 226
Book Description
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 226
Book Description
Making Jet Engines in World War II
Author: Hermione Giffard
Publisher: University of Chicago Press
ISBN: 022638862X
Category : Science
Languages : en
Pages : 362
Book Description
Our stories of industrial innovation tend to focus on individual initiative and breakthroughs. With Making Jet Enginesin World War II, Hermione Giffard uses the case of the development of jet engines to offer a different way of understanding technological innovation, revealing the complicated mix of factors that go into any decision to pursue an innovative, and therefore risky technology. Giffard compares the approaches of Britain, Germany, and the United States. Each approached jet engines in different ways because of its own war aims and industrial expertise. Germany, which produced more jet engines than the others, did so largely as replacements for more expensive piston engines. Britain, on the other hand, produced relatively few engines—but, by shifting emphasis to design rather than production, found itself at war's end holding an unrivaled range of designs. The US emphasis on development, meanwhile, built an institutional basis for postwar production. Taken together, Giffard's work makes a powerful case for a more nuanced understanding of technological innovation, one that takes into account the influence of the many organizational factors that play a part in the journey from idea to finished product.
Publisher: University of Chicago Press
ISBN: 022638862X
Category : Science
Languages : en
Pages : 362
Book Description
Our stories of industrial innovation tend to focus on individual initiative and breakthroughs. With Making Jet Enginesin World War II, Hermione Giffard uses the case of the development of jet engines to offer a different way of understanding technological innovation, revealing the complicated mix of factors that go into any decision to pursue an innovative, and therefore risky technology. Giffard compares the approaches of Britain, Germany, and the United States. Each approached jet engines in different ways because of its own war aims and industrial expertise. Germany, which produced more jet engines than the others, did so largely as replacements for more expensive piston engines. Britain, on the other hand, produced relatively few engines—but, by shifting emphasis to design rather than production, found itself at war's end holding an unrivaled range of designs. The US emphasis on development, meanwhile, built an institutional basis for postwar production. Taken together, Giffard's work makes a powerful case for a more nuanced understanding of technological innovation, one that takes into account the influence of the many organizational factors that play a part in the journey from idea to finished product.