NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Flutter Testing TechniquesDevelopments in methodology and data analysis techniques for flutter testing in flight and on the ground are discussed.
Document ID
19770014078
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Date Acquired
September 3, 2013
Publication Date
January 1, 1976
Subject Category
Aeronautics (General)
Report/Patent Number
NASA-SP-415
Report Number: NASA-SP-415
Accession Number
77N21022
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19770014079WorkOn identifying frequencies and damping in subcritical flutter testing19770014080WorkCurve fitting of aeroelastic transient response data with exponential functions19770014081WorkDetermination of subcritical damping by moving-block/randomdec applications19770014082WorkTransient excitation and data processing techniques employing the fast fourier transform for aeroelastic testing19770014083WorkTurbulence excited frequency domain damping measurement and truncation effects19770014084WorkSpecification of inputs and instrumentation for flutter testing of multivariable systems19770014085WorkSome experience using subcritical response methods in wind-tunnel flutter model studies19770014086WorkWind tunnel investigation of supersonic wing-tail flutter19770014087WorkThe design, analysis, and testing of a low-budget wind-tunnel flutter model with active aerodynamic controls19770014088WorkCorrelation with flight of some aeroelastic model studies in the NASA Langley transonic dynamics tunnel19770014089WorkTime Series Analysis in Flight Flutter Testing at the Air Force Flight Test Center: Concepts and Results19770014090WorkFlight flutter testing technology at Grumman19770014091WorkThe application of digital computers to near-real-time processing of flutter test data19770014092WorkThe Application of Recent Techniques in Flight Flutter Testing19770014093WorkF-15 flight flutter test program19770014094WorkYF-16 flight flutter test procedures19770014095WorkInflight Rotor Stability Monitor19770014096WorkInvestigation of aeroelastic stability phenomena of a helicopter by in-flight shake test19770014097WorkFlight Flutter Testing of Rotary Wing Aircraft Using a Control System Oscillation Technique19770014093WorkF-15 flight flutter test program19770014089WorkTime Series Analysis in Flight Flutter Testing at the Air Force Flight Test Center: Concepts and Results19770014097WorkFlight Flutter Testing of Rotary Wing Aircraft Using a Control System Oscillation Technique19770014091WorkThe application of digital computers to near-real-time processing of flutter test data19770014085WorkSome experience using subcritical response methods in wind-tunnel flutter model studies19770014084WorkSpecification of inputs and instrumentation for flutter testing of multivariable systems19770014095WorkInflight Rotor Stability Monitor19770014088WorkCorrelation with flight of some aeroelastic model studies in the NASA Langley transonic dynamics tunnel19770014081WorkDetermination of subcritical damping by moving-block/randomdec applications19770014094WorkYF-16 flight flutter test procedures19770014096WorkInvestigation of aeroelastic stability phenomena of a helicopter by in-flight shake test19770014092WorkThe Application of Recent Techniques in Flight Flutter Testing19770014080WorkCurve fitting of aeroelastic transient response data with exponential functions19770014090WorkFlight flutter testing technology at Grumman19770014086WorkWind tunnel investigation of supersonic wing-tail flutter19770014079WorkOn identifying frequencies and damping in subcritical flutter testing19770014082WorkTransient excitation and data processing techniques employing the fast fourier transform for aeroelastic testing19770014087WorkThe design, analysis, and testing of a low-budget wind-tunnel flutter model with active aerodynamic controls19770014083WorkTurbulence excited frequency domain damping measurement and truncation effects
No Preview Available