Three examples of response surface modeling with CFD are presented for combined cycle propulsion components. The examples include a mixed-compression-inlet during hypersonic flight, a hydrogen-fueled scramjet combustor during hypersonic flight, and a ducted-rocket nozzle during all-rocket flight. Three different experimental strategies were examined, including full factorial, fractionated central-composite, and D-optimal with embedded Plackett-Burman designs. The response variables have been confined to integral data extracted from multidimensional CFD results. Careful attention to uncertainty assessment and modeling bias has been addressed. The importance of automating experimental setup and effectively communicating statistical results are emphasized.
Response Surface Modeling of Combined-Cycle Propulsion Components using Computational Fluid Dynamics
40th Aerospace Sciences Meeting and Exhibit ; 2002 ; Reno, NV, United States
2002-03-01
Report
Keine Angabe
Englisch
Validation Database for Propulsion Computational Fluid Dynamics
Online Contents | 1997
|Hypersonic Combined Cycle Propulsion
NTIS | 1990