Mark Potsdam

Learn More
The overset grid methodology has significantly reduced time-to-solution of high-fidelity computational fluid dynamics (CFD) simulations about complex aerospace configurations. The solution process resolves the geometrical complexity of the problem domain by using separately generated but overlapping structured discretization grids that periodically exchange(More)
This work couples a computational fluid dynamics (CFD) code and rotorcraft computational structural dynamics (CSD) code to calculate helicopter rotor airloads across a range of flight conditions. An iterative loose (weak) coupling methodology is used to couple the CFD and CSD codes on a per revolution, periodic basis. The CFD uses a high fidelity,(More)
This paper describes installed rotor performance computations for the CH-47 Chinook tandem-rotor helicopter. The computations were performed with a Reynolds-Averaged Navier-Stokes flow solver using overset structured grids to resolve the flow around the rotors, the fuselage, and the resulting rotor wake system. The calculations model all six rotor blades(More)
The US Army Aeroflightdynamics Directorate (AFDD), the French Office National d’Etudes et de Recherches Aérospatiales (ONERA) and the Georgia Institute of Technology (GIT) are working under the United States/France Memorandum of Agreement on Helicopter Aeromechanics to study rotorcraft aeromechanics issues of interest to both nations. As a task under this(More)
The flowfield around a helicopter's spinning rotor, whether in forward flight or hover, is difficult to model due to the presence of unsteady flow and strong vorticity. Unlike a fixed-wing aircraft, which leaves its deposited wake behind it, a helicopter flies completely within its own strong vortex wake system. In hover, the strong tip vortices coil(More)
Downwash and outwash characteristics of a model-scale tandem-rotor system in the presence of the ground were analyzed by identifying and understanding the physical mechanisms contributing to the observed flow field behavior. A building block approach was followed in simplifying the problem, separating the effects of the fuselage, effects of one rotor on the(More)
To address the complex multidisciplinary nature of rotorcraft analysis, high-fidelity computational fluid and structural dynamics models have been developed to investigate a range of challenging rotorcraft issues. First, an advanced technology, active flap rotor (Boeing SMART) is investigated, and performance, aerodynamic and structural loads, vibration,(More)
NASA/Army UH-60A Airloads Program flight test and full-scale UH-60A Airloads wind tunnel test data are investigated in order to better understand and predict the chord bending moments, one of the unresolved issues in the UH-60A rotor loads prediction. Coupled Helios/RCAS analysis is performed and the calculated rotor loads are compared with the test data.(More)
To address the complex multidisciplinary nature of rotorcraft analysis, high-fidelity computational fluid and structural dynamics models have been developed for an advanced technology, active flap rotor. Comparisons are made between computational fluid dynamics/ computational structural dynamics, comprehensive (lifting-line, free-wake) analyses, and(More)
  • 1