Fifty Years of Flight Research
Fifty Years of Flight Research

Author: David F. Fisher

Publisher:

Published: 1999

Total Pages: 526

ISBN-13:

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A bibliography of Technical Reports from Dryden Research Center, 1946-1996. Dryden was a National Advisory Committee for Aeronautics (NACA) facility from to 1946-1958, when NACA became NASA (National Aeronautics and Space Administration). This bibliography encompasses both NACA and NASA publications. Illustrated with diagrams and photos. Black and white version.

Flight Test Techniques
Flight Test Techniques

Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Flight Mechanics Panel

Publisher:

Published: 1972

Total Pages: 266

ISBN-13:

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Investigation of Coaxial Jet Noise and Inlet Choking Using an F-111A Airplane
Investigation of Coaxial Jet Noise and Inlet Choking Using an F-111A Airplane

Author: Terrill W. Putnam

Publisher:

Published: 1973

Total Pages: 38

ISBN-13:

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Measurements of engine noise generated by an F-111A airplane positioned on a thrustmeasuring platform were made at angles of 0 deg to 160 deg from the aircraft heading. Sound power levels, power spectra, and directivity patterns are presented for jet exit velocities between 260 feet per second and 2400 feet per second. The test results indicate that the total acoustic power was proportional to the eighth power of the core jet velocity for core exhaust velocities greater than 300 meters per second (985 feet per second) and that little or no mixing of the core and fan streams occurred. The maximum sideline noise was most accurately predicted by using the average jet velocity for velocities above 300 meters per second (985 feet per second). The acoustic power spectrum was essentially the same for the single jet flow of afterburner operation and the coaxial flow of the nonafterburning condition. By varying the inlet geometry and cowl position, reductions in the sound pressure level of the blade passing frequency on the order of 15 decibels to 25 decibels were observed for inlet Mach numbers of 0.8 to 0.9.