The Busemann Advanced Concepts Laboratory has access to many facilities, ranging from computational to test and integration to flight. We have expert research associates that work together to find the most effective ways to obtain solutions to complex high-speed vehicle problems.
The students in the BAC Lab have access to a number of computational resources depending on the need. Four-core AMD Opteron workstations are used for light-to-moderate computing tasks.
Additionally, the BAC Lab has a small private cluster named CHyMP (Colorado Hypersonic MDAO Platform) which consists of 128 AMD opteron processors on an Infiniband network with 512 GB of RAM. We figure if the old infinite monkey adage of "a million chimps on a million typewriters could produce a work of William Shakespeare" was true, how much better is one really smart CHyMP working the problems at about 1 teraflop.
For larger jobs, the campus JANUS Supercomputer is available, consisting of 16,416 available cores with 32 TB of total system RAM and can achieve 184 teraflops.
The BAC Lab has done extensive testing on its miniature turbojet. There have been three different test stands developed over the years, with the Fluid Extraction for Nozzle Injection eXperiment (FENIX) being the latest one. FENIX is an experimental test bed that supports thrust vectoring and supersonic throat constriction experiments. The test stand was designed by seniors in the 2011-2012 school year. The stand can measure force in all three dimensions to measure fluidic thrust vectoring for yaw, pitch, and roll control. The current test stand is adapted for the AT-450 miniature turbojet, but can be adapted to any miniature turbojet.
With the various test stands, the laboratory has been able to characterize performance to verify several engine cycle codes. This includes creating and analyzing augmentations to the engine, such as the afterburner and variable area nozzle.
The Supersonic Wind and Imaging Flow Tunnel (SWIFT) is a blowdown tunnel with capabilities from subsonic up to Mach 3+ flows (interchangeable nozzles for Mach 1.5, 2.0, 2.5, and 3.0 ± 0.05).
This is a desktop size wind tunnel, shown in the CAD representation, which makes it very amiable to student involvement. It was recently modified to facilitate fluidic injection testing for both throat constriction and throat skewing type thrust vectoring. It is equipped with a Schlieren photograph system and is capable of a run time of greater than 5 sec of steady state flow.
Its capacity is capable of 6 runs at Mach 2 without changing the reservoir. It runs with a computer controlled LabView interface to regulate injector pressure and mass flow rate relative to the primary nozzle conditions. Additional instrumentation includes pressure transducers, thermocouples, digital pressure regulators, etc. connected to a National Instruments cRIO data acquisition system.