TRANSIENT AND NONLINEAR EFFECTS ON HIGH SPEED, VIBRATORY, THERMOELASTIC INSTABILITY PHENOMENA
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1960
- Accession Number
- AD0266375
Entities
People
- Eugene J. Jr. Brunelle
Organizations
- Massachusetts Institute of Technology