US 12,421,919 B2
Inlets for hypersonic air-breathing vehicles and design methods and systems therefor
Mark Edward Noftz, Villa Park, IL (US); Joseph Stephen Jewell, West Lafayette, IN (US); Andrew James Shuck, Indianapolis, IN (US); Jonathan Poggie, West Lafayette, IN (US); Andrew Nixon Bustard, South Bend, IN (US); and Thomas James Juliano, Granger, IN (US)
Assigned to Purdue Research Foundation, West Lafayette, IN (US); and University of Notre Dame Du Lac, South Bend, IN (US)
Filed by Purdue Research Foundation, West Lafayette, IN (US); and University of Notre Dame du Lac, South Bend, IN (US)
Filed on Dec. 23, 2023, as Appl. No. 18/395,513.
Application 18/395,513 is a continuation of application No. 18/240,818, filed on Aug. 31, 2023.
Claims priority of provisional application 63/402,570, filed on Aug. 31, 2022.
Prior Publication US 2024/0352907 A1, Oct. 24, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02K 7/10 (2006.01)
CPC F02K 7/10 (2013.01) 12 Claims
OG exemplary drawing
 
1. A computer-implemented method of generating a design of an inlet for a hypersonic air breathing vehicle using a processor system comprising a plurality of CPUs, the method comprising:
solving in parallel on a plurality of free CPUs in the processor system for unique Busemann contour solutions from Taylor-Maccoll equations for conical flow in each of a plurality of osculating planes over an azimuthal sweep of a hypothetical inlet shape by changing boundary conditions; and
generating streamtraces of the inlet, the streamtraces comprising a streamtrace of the inlet from the unique Busemann contour solution in each osculating plane, the streamtraces collectively defining a shape of the inlet; and
generating the design of the inlet to have the shape defined by the streamtraces.