Fulcrum utilizes state-of-the-art computational fluid dynamics (CFD) modeling techniques to provide in-depth aerodynamic analysis. Flight science engineers at Fulcrum bring years of experience simulating fluid flow for a wide variety of applications. These include analysis of turbomachinery components, external aerodynamics of modifications to fixed and rotary-wing aircraft, and safe separation / jettison analysis. The team employs STAR-CCM+, a leading commercial CFD package, on a cloud-based, scalable HPC service to simulate fluid flows and deliver product insights. Traditional physics models are utilized for aerodynamic loads analysis, design studies, and efficiency calculations. Depending on project requirements, Fulcrum leverages experience with more advanced modeling techniques, including dynamic fluid body interaction (DFBI), fluid-structure interaction (FSI), conjugate heat transfer (CHT), discrete phase modeling (DPM), and acoustic analysis. The Fulcrum flight sciences team delivers results to inform key design decisions, validate existing hardware, and explore critical regions of the solution space.
The shape of the GP-19 was designed with the aid of aerodynamic analysis at several anticipated flight points using STAR-CCM+ CFD software. Aerodynamic load data is provided to the stress team for FEM analysis. Cooling considerations were investigated with internal flow models.
Aerodynamic analysis drove the design of the B429 fairings. Wing leading edge (LE)/trailing edge (TE) fairings chosen for minimal drag and flow separation from 2D models run at wide variety of conditions and angles of attack. Full-fidelity, 3D CFD models investigated interference drag effects of root fairing designs with the fuselage and skids.
Without a deflector on the aft end of the jump rocket launcher, the MK-66 exhaust plume impinges on the ground, becoming a hazard to the environment. Hypersonic CFD models of the exhaust aid the design of an aft deflector to protect the surroundings without significant impact to the rocket launch capability or structural integrity of the launcher.
Safe Separation/Jettison Analysis
C-12 Wing Locker ALE Support System (ALESS)
Safe separation analysis aims to identify the flight envelope for which a store can be launched from an aircraft safely, without striking the aircraft or excessive tumbling. It also aids flight testing by narrowing the test case matrix to flight regimes deemed critical by the analysis. CFD data shows safe separation of the ALTIUS from the modified C-12 wing locker. Trajectory predictions closely match with flight test data.