Numerical Study of Transonic Flow Characteristics Around a Compound Delta Wing
Disciplines
Aerodynamics and Fluid Mechanics
Abstract (300 words maximum)
This study numerically investigates the aerodynamic performance of a compound delta wing featuring multiple leading-edge sweep angles to optimize transonic flight characteristics. Inspired by the HAL Tejas wing design, the compound leading-edge configuration is designed to reduce wave drag while maintaining lift across a broad flight envelope. Computational fluid dynamics (CFD) simulations were performed at Mach numbers 0.75, 0.85, 0.95, 1.0, and 1.1, with angles of attack ranging from 0° to 55°. The unsteady Reynolds-averaged Navier–Stokes (URANS) approach, coupled with the Spalart–Allmaras turbulence model, was employed for its accuracy in resolving transonic aerodynamic flows at a reasonable computational cost. The numerical methodology was validated against experimental data through comparisons of surface pressure distributions and lift coefficients of delta wings. The aerodynamic performance of the compound delta wing was benchmarked against a baseline single-sweep delta wing to evaluate improvements in efficiency. Results reveal a notable reduction in drag, particularly at Mach 1, with decreases of 17.38%, 12.50%, and 13.25% at angles of attack of 5°, 30°, and 55°, respectively. While the maximum lift coefficient exhibited a slight reduction of 3.58%, the lift-to-drag ratio improved by 11.10%, 14.89%, and 7.24% at the same angles, demonstrating enhanced aerodynamic efficiency in the transonic regime. These findings highlight the potential of the compound delta wing configuration to improve transonic aircraft performance by mitigating drag penalties while preserving favorable lift characteristics.
Academic department under which the project should be listed
SPCEET - Mechanical Engineering
Primary Investigator (PI) Name
Gaurav Sharma
Numerical Study of Transonic Flow Characteristics Around a Compound Delta Wing
This study numerically investigates the aerodynamic performance of a compound delta wing featuring multiple leading-edge sweep angles to optimize transonic flight characteristics. Inspired by the HAL Tejas wing design, the compound leading-edge configuration is designed to reduce wave drag while maintaining lift across a broad flight envelope. Computational fluid dynamics (CFD) simulations were performed at Mach numbers 0.75, 0.85, 0.95, 1.0, and 1.1, with angles of attack ranging from 0° to 55°. The unsteady Reynolds-averaged Navier–Stokes (URANS) approach, coupled with the Spalart–Allmaras turbulence model, was employed for its accuracy in resolving transonic aerodynamic flows at a reasonable computational cost. The numerical methodology was validated against experimental data through comparisons of surface pressure distributions and lift coefficients of delta wings. The aerodynamic performance of the compound delta wing was benchmarked against a baseline single-sweep delta wing to evaluate improvements in efficiency. Results reveal a notable reduction in drag, particularly at Mach 1, with decreases of 17.38%, 12.50%, and 13.25% at angles of attack of 5°, 30°, and 55°, respectively. While the maximum lift coefficient exhibited a slight reduction of 3.58%, the lift-to-drag ratio improved by 11.10%, 14.89%, and 7.24% at the same angles, demonstrating enhanced aerodynamic efficiency in the transonic regime. These findings highlight the potential of the compound delta wing configuration to improve transonic aircraft performance by mitigating drag penalties while preserving favorable lift characteristics.