Effect of Amplitude and Mean Angle of Attack on the Unsteady Surface Pressure of a Pitching Airfoil

Mohammad Reza Dr. Soltani

Volume 2, Issue 4 , December 2005, Pages 9-26

  Details of pressure distributions, on a two dimensional airfoil oscillating in pitch through stall, in a 0.8 0.8 m low-speed wind tunnel are presented. Pitching occurred about the airfoils quarter-chord axis. Pitch rate, Reynolds number, and oscillation amplitudes were varied to determine the effects ...  Read More

Robust Optimal Control of Flexible Spacecraft During Slewing Maneuvers

Aliakbar Dr. Moosavian

Volume 2, Issue 4 , December 2005, Pages 37-43

  In this paper, slewing maneuver of a flexible spacecraft with large angle of rotation is considered and assuming structural frequency uncertainties a robust minimum-time optimal control law is developed. Considering typical bang-bang control commands with multiple symmetrical switches, a parameter optimization ...  Read More

Transonic and Supersonic Overtaking of a Projectile Preceding a Shock Wave

H. Ahmadikia; Ebrahim Dr. Shirani

Volume 2, Issue 4 , December 2005, Pages 45-53

  In this paper, two-dimensional and axisymmetric, time dependent transonic and supersonic flows over a projectile overtaking a moving shock wave are considered. The flow is simulated numerically by solving full time averaged Navier-Stokes equations. The equations are linearized by Newton approach. The ...  Read More

Orr Sommerfeld Solver Using Mapped Finite Di?erence Scheme for Plane Wake Flow

Mohammad Javad Maghrebi

Volume 2, Issue 4 , December 2005, Pages 55-63

  Linear stability analysis of the three dimensional plane wake flow is performed using a mapped finite di?erence scheme in a domain which is doubly infinite in the cross–stream direction of wake flow. The physical domain in cross–stream direction is mapped to the computational domain using a cotangent ...  Read More