Low Cost Aircraft Flutter Clearance
Low Cost Aircraft Flutter Clearance

Author: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (France)

Publisher:

Published: 1979

Total Pages: 115

ISBN-13:

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Light aircraft and gliders are constructed by small manufacturers who do not have the manpower or financial resources to evaluate flutter safety with the costly modern sophisticated test and analysis techniques available to large companies. Future low cost reconnaissance, liaison, RPV and other military aircraft could be designed and built by such small aircraft manufacturers. This Specialists Meeting was therefore held to evaluate the usage of low cost aircraft flutter clearance procedures. Some results occurring from such procedures (weight efficiency, safety, flight incidents, and overall costs) were discussed relative to those from methods using advanced state-of-the-art. The relative technological-financial position of the small lightweight aircraft manufacturer was also discussed. The difficulties that still exist and the progress to be expected in the next few years were exposed.

Scientific and Technical Aerospace Reports
Scientific and Technical Aerospace Reports

Author:

Publisher:

Published: 1995

Total Pages: 652

ISBN-13:

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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Flutter Clearance of the F-14a Variable-Sweep Transition Flight Experiment Airplane, Phase 2
Flutter Clearance of the F-14a Variable-Sweep Transition Flight Experiment Airplane, Phase 2

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-07-03

Total Pages: 46

ISBN-13: 9781722244378

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An F-14A aircraft was modified for use as the test-bed aircraft for the variable-sweep transition flight experiment (VSTFE) program. The VSTFE program was a laminar flow research program designed to measure the effects of wing sweep on laminar flow. The airplane was modified by adding an upper surface foam and fiberglass glove to the right wing. An existing left wing glove had been added for the previous phase of the program. Ground vibration and flight flutter testing were accomplished to verify the absence of aeroelastic instabilities within a flight envelope of Mach 0.9 or 450 knots, calibrated airspeed, whichever was less. Flight test data indicated satisfactory damping levels and trends for the elastic structural modes of the airplane. Ground vibration test data are presented along with in-flight frequency and damping estimates, time histories and power spectral densities of in-flight sensors, and pressure distribution data. Freudinger, Lawrence C. and Kehoe, Michael W. Armstrong Flight Research Center RTOP 505-60-31...