Book Description
The report outlines work performed in support of the flowpath development for the DRACO engine program. The design process initiated to develop a hypersonic axisymmetric inlet for a Mach 6 rocket-based combined cycle (RBCC) engine is discussed. Various design parametrics were investigated, including design shock-on-lip Mach number, cone angle, throat Mach number, throat angle. length of distributed compression, and subsonic diffuser contours. Conceptual mechanical designs consistent with installation into the D-21 vehicle were developed. Additionally, program planning for an intensive inlet development program to support a Critical Design Review in three years was performed. This development program included both analytical and experimental elements and support for a flight-capable inlet mechanical design.Sanders, Bobby W. and Weir, Lois J.Marshall Space Flight CenterHYPERSONIC INLETS; DESIGN ANALYSIS; ROCKET-BASED COMBINED-CYCLE ENGINES; ROCKET ENGINE DESIGN; FLOW DISTRIBUTION; THROATS; MACH NUMBER; PROJECT PLANNING; FUNCTIONAL DESIGN SPECIFICATIONS