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Kuo, C.-C.

Publications and source records attributed to Kuo, C.-C..

6 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1976

Some considerations of the dynamics of Space Shuttle vehicle thermal protection system

Two types of reusable surface insulation under consideration for Space Shuttle applications have been analyzed for flutter stability. The first consisted of silicone rubber-coated Nomex felt bonded to the skin of the vehicle; the second consisted of silicone tiles with ceramic coating on five faces, bonded to Nomex felt which was then attached to the vehicle skin. The piston theory was used to compute the aerodynamic forces on the basis of simple models on the two systems. Exact solutions were obtained, and the effect of different parameters of the flutter stability boundary was investigated. Possible reasons for the slow convergence of the Galerkin technique for analyzing membrane flutter are suggested, and a consistent set of nondimensional parameters convenient for flutter studies is introduced.

Kuo, C.-C.↗
NASA NTRS1974

Subsonic potential aerodynamics for complex configurations - A general theory

A general theory of subsonic potential aerodynamic flow around a lifting body having arbitrary shape and motion is presented. By using the Green function method, an integral representation for the velocity potential is obtained for both supersonic and subsonic flow. Under the small perturbation assumption, the potential at any point in the field depends only upon the values of the potential and its normal derivative on the surface of the body. On the surface of the body, this representation reduces to an integro-differential equation relating the potential and its normal derivative (which is known from the boundary conditions) on the surface. The theory is applied to finite-thickness wings in subsonic steady and oscillatory flows.

Morino, L.↗
NASA NTRS1973

Unsteady subsonic compressible flow around finite thickness wings.

A general formulation for the unsteady subsonic compressible potential flow around aircraft having arbitrary configurations is presented. An integral representation of the velocity potential is obtained. From this a linear integral equation relating the perturbation potential and its normal derivative (which is known from the boundary conditions) is derived. For the numerical solution of the integral equation, the surface of the aircraft is divided into small elements and the potential is assumed to be constant within each element. Numerical results are obtained for an oscillating finite-thickness wing and indicate good convergence and excellent agreement with existing lifting surface solutions.

Morino, L.↗
NASA NTRS1972

Perturbation and harmonic balance methods for nonlinear panel flutter.

A systematic way of applying both perturbation methods and harmonic balance methods to nonlinear panel flutter problems is developed here. Results obtained by both these methods for two-dimensional simply supported and three-dimensional clamped-clamped plates with six modes agree well with those obtained by the straightforward direct integration method, yet require less computer time and provide better insight into the solutions. Effects of viscoelastic structural damping on the flutter stability boundary are generally found to be destabilizing and the postflutter behavior becomes more explosive. The methods developed here may be of interest in related vibration problems.

Kuo, C.-C.↗