The overall objective of this proposal is to develop a tool that integrates and optimizes the design of internal scramjet engine flowlines with external aerodynamic designs of hypersonic vehicles. The design of non-optimal, manual iteration engine-integrated inward turning scramjets with waverider… More

In the last few years, the renewed development of inward-turning scramjets with vehicle conformal nozzle shapes for both cruise vehicle and accelerators has led to the need for new combined cycle integration strategies for both turbine and rocket engine systems. Strategies must be developed which… More

This SBIR presents an opportunity to study alternate scramjet engine configurations in an effort to increase spillage to levels between inward-turning and planar inlets while understanding the impact on engine and vehicle performance from a systems level perspective. To accomplish this, our team… More

The work proposed here provides an opportunity to take what we have learned within the DARPA Falcon program on TBCC inlet design and our current AF RBCC/TBCC nozzle research and integrate them into our Propulsion-Airframe Integration (PAI) tool, Eco. Once integrated into Eco, representative TBCC… More

The proposed Phase I SBIR seeks to develop passive self-starting inlet technologies and extend inlet operability to a range of at least 3 Mach numbers. This development will be completed using GHI's design and optimization tools and will be validated with the experimental testing of a self-starting… More

This SBIR gives GHI the chance to evolve our measurement techniques within our overarching design-to-test process. If we can develop rapid instrumentation design methods and techniques that can enable us to quickly evaluate and fix problems with existing designs and quickly develop new designs with… More

The two main objectives of this proposal are to refine the combined cycle engine capabilities in GHIs design tool, Eco, and to flight test a combined cycle powered vehicle concept designed for flight in the Mach 0-4 range. Tools will be created to permit high-fidelity conceptual designs, including… More

At hypersonic flow conditions, the flow field around reentry vehicles is ionized, resulting in electro-optical emissions, detectable radar cross-sections, and attenuation of signals transmitted through the plasma. Ablative heat shields may further increase the levels of electrons in the plasma… More

ABSTRACT: This SBIR program provides the GHI team with the opportunity to integrate state-of-the-art Computational Fluid Dynamics (CFD) codes into a scramjet engine analysis tool that will enable the rapid design, simulation, and optimization of scramjet engines within an airframe-integrated… More

ABSTRACT: GoHypersonic Inc. is proud to present the following Phase II SBIR Proposal to the AFRL/RZA involving the development, fabrication, and testing of a high-performing flight-capable self-starting scramjet inlet. Under our Phase I SBIR work, we have developed and validated a self-starting… More

During hypersonic reentry, the flow around reentry vehicles is ionized resulting in electro-optical and infrared emissions, detectable radar cross-sections, and attenuation of signals transmitted through the plasma. Modeling these flows requires both expertise and substantial user time. The Phase II… More