columbus · Flutter Model Tests Of A Swept-back, All-moving Horizontal Tail At Supersonic Speeds

Flutter Model Tests Of A Swept-back, All-moving Horizontal Tail At Supersonic Speeds

Title: Flutter Model Tests Of A Swept-back, All-moving Horizontal Tail At Supersonic Speeds
Date: 1957
Index Abstract: Coming Soon
Photo Quality: Complete
Report Number: WADC TR 56-285
Corporate Author: Massachusetts Inst Of Tech Cambridge
Laboratory: Aircraft Laboratory
Extent: 64
NTRL Accession Number: AD142088
Identifier: AD0142088
Access Rights: ASTIA
Distribution Classification: 1
Contract: AF 33(616)-2751
DoD Project: 1370
DoD Task: 13479
DTIC Record Exists: No
Distribution Change Authority Correspondence: Air Force Flight Dynamics Lab ltr
Abstract: This report describes the flutter testing at supersonic speeds of a series of swept-back all-moving stabilizers. An attempt was made to define the flutter boundaries, for one location of the pitching axis, over the Mach number range of 1.3 to 2.1, by testing at a number of different levels of stabilizer stiffness, and at a number of different pitching frequencies. The results indicate that large increases in the region of instability can occur due to the introduction of the pitching degrees of freedom. The test results follow the trends of theoretical calculations, but the quantitative correlation between the theoretical and the experimental results is only fair.
Report Availability: Full text available
Date Issued: 1957-11
Provenance: Lockheed Martin Missiles & Fire Control
Type: report
Format: 1 online resource
Creator: Asher, Gifford W.