by National Aeronautics and Space Administration, Glenn Research Center, Available from National Technical Information Service in Cleveland, Ohio, Springfield, VA .
Written in English
|Statement||C. Lawrence, E. Spyropoulos, T.S.R. Reddy.|
|Series||NASA/TM -- 2000-209635., NASA technical memorandum -- 209635.|
|Contributions||Spyropoulos, E., Reddy, T. S. R., NASA Glenn Research Center.|
|The Physical Object|
Additional Physical Format: Online version: Lawrence, Charles, Unsteady cascade aerodynamic response using a multiphysics simulation code (OCoLC) The multiphysics code Spectrum(TM) is applied to calculate the unsteady aerodynamic pressures of oscillating cascade of airfoils representing a blade row of a turbomachinery component. DEVELOPMENT OF UNSTEADY AERODYNAMIC AND AEROELASTIC REDUCED-ORDER MODELS USING THE FUN3D CODE Walter A. Silva1, Veer N. Vatsa2, and Robert T. Biedron2 1Aeroelasticity Branch @ 2Computational Aerosciences Branch NASA Langley Research Center Hampton, Virginia Keywords. FUN3D, ROM, aeroelasticity, utter, root locus Cited by: 8. Numerical Simulations of Unsteady, Viscous, 1 c unsteady flow in a cascade. The use of a deforming grid simplifies the speci- nate system in strong conservation form using an AD1 procedure. code uses the same AD1 procedure to solve for the interior of the computational.
Modeling of Unsteady Aerodynamic Loads. The CFD computations were carried out using a multi-block structured RANS code based on an implicit finite volume algorithm to solve the time averaged. Numerical modeling of inviscid compressible gas flow past a linear cascade of airfoils executing small harmonic translational and rotational vibrations is carried out. The control volume method on moving unstructured grid structures is used for discretization of basic equations. The influence of the frequency and phase characteristics of the airfoils on the pressure distribution over their Author: K. N. Volkov. Ver77] J. M. Verdon. Further developments in the aerodynamic analysis of unsteady supersonic cascades, i. the unsteady pressure field, ii. aerodynamic response predictions. Trans. ASME A: J. Engng for Power, 99 (4): , CrossRef Google ScholarCited by: 5. Unsteady aerodynamics modeling for aircraft maneuvers: A new approach for computing the unsteady and nonlinear aerodynamic loads acting on a maneuvering The transient aerodynamic response due to a unit step change in a forcing parameter, such as angle of attack or pitch rate is a.
Maneuvers were generated from a time-optimal prediction code using a derivative-based aerodynamic model. In these maneuvers, the angular rates at the initial time were assumed to be zero. Static and dynamic derivatives were estimated from response function values at the final time, where the response function reaches a steady-state by: Development of an Unsteady Aerodynamic Simulator Using Large-Eddy Simulation Based on High-Performance Computing Technique A numerical method specially designed to predict unsteady aerodynamics of road vehicle was developed based on unstructured Large-Eddy Simulation (LES) by: The use of numerical simulation, and more specifi cally multiphysics modeling, is prevalent throughout the Innovation and Technology group. “Actually, all of our products and applications have seen the use of multiphysics simulation,” says Ryan Paul, Innovation & Technology Manager at GrafTech. Figure Size: 4MB. Under consideration for publication in J. Fluid Mech. 1 Estimation of unsteady aerodynamic forces using pointwise velocity data F. G omez1y, A. S. Sharma2 and H. M. Blackburn1 1Dept. of Mechanical and Aerospace Engineering, Monash University, VIC , Australia 2Aerodynamics and Flight Mechanics, University of Southampton, Southampton SO17 1BJ, UKFile Size: 1MB.