MUMBAI, India, Sept. 14 -- Intellectual Property India has published a patent application (202641101834 A) filed by T. Kumarasan; Elphej Churchil S J; S. Maria Mercy; P. Jermia Arockia Pravin; G. Subiksha; K. Nehru; and D. Rajesh Kumar on August 24, 2026, for Multi-Chevron Supersonic Exhaust Nozzle With Semi-Circular Profiles.
Inventors include T. Kumarasan; Elphej Churchil S J; S. Maria Mercy; P. Jermia Arockia Pravin; G. Subiksha; K. Nehru; and D. Rajesh Kumar.
The application for the patent was published on September 11, 2026, under issue no. 37/2026.
Abstract: An exhaust nozzle assembly for high-speed aerospace applications includes a primary nozzle body defining a central longitudinal flow axis, an upstream inlet configured to receive high pressure exhaust gas, and a downstream exit orifice terminating at a trailing circumferential edge. A plurality of chevrons is arrayed circumferentially along the trailing edge, wherein each chevron defines a smooth, convex semi-circular profile extending between adjoining base roots along the trailing circumference. The semi-circular chevrons are configured at a predetermined penetration angle (beta) between 60 and 75.5 relative to the flow axis to eliminate sharp corner vertices, reduce localized stress, and induce curved shear-layer vortex pairs. This geometry accelerates core exhaust flow from transonic speeds up to hypersonic regimes reaching Mach 5.68 while enabling targeted acoustic suppression down to 121 dB depending on chevron count (N8 or N16) and angular deflection.
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