Simulations of a 10% scale Multi-Purpose Crew Vehicle and its drogue parachute were carried out using US3D, a finite-volume computational fluid dynamics code, with capsule angles of attack at 0, 30 and 50 degrees. A model for the geometric porosity of the parachute is incorporated which locally varies the mass flux through the surface based on the instantaneous flowfield. These simulations were then compared to wind tunnel tests, including mean drag measurements and particle image velocimetry data. It was found that the simulations matched the wind tunnel drag within 4% for α = 0 and 30° with the maximum drag deficit due to the capsule being 13.4% at α = 0°. Pressure data from the simulations was used to deform a structural model of the parachute to the correct inflated shape, as a precursor to future fluid structural interaction work.
|Original language||English (US)|
|Title of host publication||AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013|
|State||Published - 2013|
|Event||22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013 - Daytona Beach, FL, United States|
Duration: Mar 25 2013 → Mar 28 2013
|Name||AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013|
|Other||22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013|
|City||Daytona Beach, FL|
|Period||3/25/13 → 3/28/13|
Bibliographical noteFunding Information:
This work was sponsored in part by NASA. Computer time was provided by the Minnesota Supercomputing Institute.