Accession Number:

AD0917346

Title:

SST Technology Follow-On Program-Phase II. Correlation of Flutter Analysis and Test Results for Half-Span SST Wing Models in Subsonic and Supersonic Flow.

Descriptive Note:

Final rept. on Task 5, May 70-May 72,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Personal Author(s):

• Ryneveld, A. D.

Report Date:

1973-06-01

Pagination or Media Count:

86.0

Abstract:

SST half-span cantilever wing flutter models have been analyzed and tested during the SST program and during the technical follow-on phase II period. One model designed for transonic flow was tested in the Langley transonic dynamics tunnel TDT. A second model, designed for supersonic flow, was tested at both the Ames 6- by 6-ft supersonic tunnel and the Langley TDT. Structural, vibration, and flutter analyses were performed for both models and the results compared with experimental data. Conclusions are that analysistest correlation is reasonably good for subsonic flow but not so good for supersonic flow conditions. Model test results remain as the primary source of transonic flutter information to guide flutter prediction in this regime.

Descriptors:

• *FLUTTER
• *VARYING SWEEP WINGS
• SUPERSONIC AIRCRAFT
• SUPERSONIC TRANSPORT AIRCRAFT
• TRANSONIC CHARACTERISTICS
• VIBRATION
• DEFLECTION
• TRAILING EDGES
• CANTILEVER BEAMS
• JET ENGINE NACELLES
• WIND TUNNEL TESTS
• WIND TUNNEL MODELS
• MATHEMATICAL MODELS
• EXPERIMENTAL DATA
• STIFFNESS
• MASS
• BALANCE
• STRUCTURAL COMPONENTS
• BEAMS(STRUCTURAL)
• DATA REDUCTION
• AIRCRAFT PANELS
• FIBERGLASS

Subject Categories:

• Aerodynamics
• Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE