Preliminary Study of Optimum Ductburning Turbofan Engine Cycle Design Parameters for Supersonic Cruising
Author:   National Aeronaut Administration (Nasa)
Publisher:   Createspace Independent Publishing Platform
ISBN:  

9781724683182


Pages:   32
Publication Date:   06 August 2018
Format:   Paperback
Availability:   Available To Order   Availability explained
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Preliminary Study of Optimum Ductburning Turbofan Engine Cycle Design Parameters for Supersonic Cruising


Overview

The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature rise on the engine weight and cruise fuel consumption for a mach 2.4 supersonic transport was investigated. Design point engines, optimized purely for the supersonic cruising portion of the flight where the bulk of the fuel is consumed, are considered. Based on constant thrust requirements at cruise, fuel consumption considerations would favor medium by pass ratio engines (1.5 to 1.8) of overall pressure ratio of about 16. Engine weight considerations favor low bypass ratio (0.6 or less) and low wverall pressure ratio (8). Combination of both effects results in bypass ratios of 0.6 to 0.8 and overall pressure ratio of 12 being the overall optimum. Fishbach, L. H. Glenn Research Center NASA-TM-79047, E-9856

Full Product Details

Author:   National Aeronaut Administration (Nasa)
Publisher:   Createspace Independent Publishing Platform
Imprint:   Createspace Independent Publishing Platform
Dimensions:   Width: 21.60cm , Height: 0.20cm , Length: 28.00cm
Weight:   0.102kg
ISBN:  

9781724683182


ISBN 10:   1724683187
Pages:   32
Publication Date:   06 August 2018
Audience:   General/trade ,  General
Format:   Paperback
Publisher's Status:   Active
Availability:   Available To Order   Availability explained
We have confirmation that this item is in stock with the supplier. It will be ordered in for you and dispatched immediately.

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