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Propulsion Flexibility Concepts Based on New Component Development

Report Number: AFOSR 69-2951TR p. 56-76
Author: Bush, H. Ivan
Corporate Author: Air Force Aero Propulsion Laboratory
Date of Publication: 1969-12

The paper briefly describes some of the potential that exists for improving mission flexibility through changes in the operating characteristics of turbine engine basic components. Mission flexibility is discussed in terms of range, radius-of-action, and fuel consumption improvements inherent in a vehicle constrained to fly three different missions. The improvements are described as a function of the degree of airflow match improvement between inlet, engine, and exhaust system. The engineering emphasis needed in each of the engine major components to improve the total propulsion system airflow match characteristics is then briefly discussed.

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