Design of an Internal Osculating Waverider Intake

Authors

• Mark E. Noftz, Purdue University
• Andrew J. Shuck, Purdue University
• Joseph S. Jewell, Purdue University
• Jonathan Poggie, Purdue University
• Andrew N. Bustard, University of Notre DameFollow
• Thomas J. Juliano, University of Notre Dame
• Nicholas J. Bisek, Air Force Research Laboratory

Submitting Campus

Daytona Beach

Department

Aerospace Engineering

Document Type

Article

Publication/Presentation Date

2023

Abstract/Description

The design of an inward-turning, high-speed, three-dimensional streamline traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and Internal Conical Flow-A solution is used as the basic isentropic compressive streamline. This new contour provides efficient compression, high flow uniformity, and straight leading edge shocks of equal strength. Additionally, a novel method for constructing the inlet cowl is presented. The combined process leads to a new method of high-speed intake design. A generic shape-transitioned intake is constructed and named the Indiana Inlet for the Indiana universities that contributed to the project. Computational fluid dynamic results are assessed to validate the design method for the two-dimensional parent flowfields and the full three-dimensional design.

Publication Title

Journal of Propulsion and Power

DOI

https://doi.org/10.2514/1.B38916

Publisher

American Institute of Aeronautics and Astronautics

Grant or Award Name

U.S. Air Force Research Laboratory award number FA8650-20-2-240

Additional Information

Dr. Bustard was not affiliated with Embry-Riddle Aeronautical University at the time this paper was published.

Scholarly Commons Citation

Noftz, M. E., Shuck, A. J., Jewell, J. S., Poggie, J., Bustard, A. N., Juliano, T. J., & Bisek, N. J. (2023). Design of an internal osculating waverider intake. Journal of Propulsion and Power, 39(3), 377-389.