Accession Number:

AD0266375

Title:

TRANSIENT AND NONLINEAR EFFECTS ON HIGH SPEED, VIBRATORY, THERMOELASTIC INSTABILITY PHENOMENA

Descriptive Note:

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB

Personal Author(s):

Report Date:

1960-12-01

Pagination or Media Count:

1.0

Abstract:

Research concerns the formulation and investigation of the equations representing the dynamic, torsion-bending motion of a wing which is one major component of an ultra-high performance manned vehicle. Preliminary work required for this investigation is included as an integral part of the report. This preliminary work includes 1 the derivation of an exact twodimensional linearized aerodynamic theory for an accelerating unsteady supersonic airfoil, 2 the re-derivation of piston theory aerodynamics for arbitrary motion, and 3 a derivation for the torsional stiffness loss of an aircraft wing that includes the effects of a specified timedependent w ll temperature due to the given flight mission and that includes the effects of mid-plane stretching. The computer studies consider super X-15 typ wing performing t o specified flight missions and provide answers in the form of pitch and plunge i pulse re ponse time histories. The exact solutions are compared wi h two approximate solutio s. Resul s indicate a quasi-steady aero-thermoelastic analysis is adequate for manned vehicles of the foreseeable future. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE