PRABHAKARAN G

Client: Safran (Aircraft Engine)

• The influence of chamfering and corner radiusing(fillet) on the discharge coefficient of rotating axial orifices for gas turbine engine applications.
• The influence of incidence angle on the discharge coefficient for rotating radial orifices.

Akkodis, India June 2023-June 2023

• Aerodynamic analysis of A350 aircraft for various flight conditions.
• Aerodynamic analysis of Beluga XL aircraft for various flight conditions.
• Drag estimation studies for turbofan nozzle configuration.

Deputation to Akkodis France June 2023-October 2023

• Gas turbofan air inlet studies for A350 and BelugaXL for various fight conditions such as windmilling, takeoff, and crosswind. The aim of the study was to ensure the flow uniformity within acceptable limits as specified by engine manufacturers

Ecosat Airship Tradeoff Analysis

• Shape optimization: Three airship configurations such as cigarette, modified glodschmied, and vane shapes were studied to identify the best configuration for station keeping mission at 20km ISA and 30 m/s.
• Stability control: Different fin configurations such as cross(+),saltire(X), and star(Y) have been analyzed in order to stability and control criteria.
• Engine Location study: The location such as the propeller on the stern, side, and keel were studied to find best possible location.
• Architecture: The concepts such as blimp vs semi-rigid, gas bags vs ballonets , postion of keel(inside vs outside), rigid tail vs inflatble tail, best place for payload bay,postion of morring to land the airship were studied and identified the best option
• Material selection: A different materials such as fabric,composite and metals were studied.
• Powerplant selection: The two option such as geared and driect drive were stuided.
• Energy harvesting: Ecosat has been planed to use solar enery for engine operation.Several types of cells from different manufatures such as alpha, beta and gamma PV has been studied.
• Payload and Trajectory study

Client: OFB, Gov. of India, Nagpur

• Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes.
• Hold complete responsibility for Customer support and training customers on ANSYS CFD problems.
• Executing customer projects using CFD tools predominantly with ANSYS.

Preliminary design of Unmanned Combat Aerial Vehicle (UCAV) -SWIFT-GHATAK

• Air inlet study: The study was carried out at critical points to ensure the flow uniformity (DC90) within acceptable limits as specified by the engine manufacturer.
• Air data boom sensor position error study(Pt,P,AOA, and AOSS vane ): The different length boom study was carried out to select the best configuration.
• Aerodynamic data generation: The analysis was carried out to generate the stability derivative and control derivate.
• Hinge moment study for actuator selection: To estimate the actuator requirements, hinge moment are required for elevons and spoilers.
• Performance studies: The parameters like range, endurance and takeoff distance were calculated

Paper Presentation:

“Position Error Studies for Air data Boom of Flying Wing Configuration using RANS CFD Simulation” was presented at 20th Annual CFD Symposium conducted by Aeronautical Society of India –CFD Division

Aerodynamic interference between high-speed slender bodies(for mid air refueling Application).

The quantitative study was carried out to determine and interpret the interference between two slender bodies. Computational Fluid Dynamics (CFD) was used extensively to interpret the measured trends and understand the underlying aerodynamics of the interference flow field. Therefore, the aerodynamics of geometric configuration at different angles of attack are investigated and the interference effects are evaluated and validated with experimental results

Paper Presentation:

“Computational Study of Aerodynamic Interference Flow Field at High Speeds” was presented at 18th Annual CFD Symposium conducted by Aeronautical Society of India –CFD Division.

• Analysis of internal performance of canister during missile launching. The quantitative study was carried out to determine the missile motion inside the canister during launching. This study includes the estimation of time for the missile's initial movement within the canister and the total time it takes to exit the canister. Complex methods such as UDF, Hybrid, and dynamic meshing options are used to capture the unsteady phenomenon.
• Wind tunnel studies for various aerospace configurations

The analysis was carried to estimate the longitudinal and lateral aerodynamic characteristics for various flight conditions

Airborne Early Warning Control Systems (AWE&C)

• External aerodynamics analysis of "Active Antenna Array Control Unit (AAAU)'' components.
• Altitude Effect on Inlet Velocity of AAAU on Embraer 144 Aircraft
• Effect of fuselage and SATCOM on AAAU inlet of Embraer 144 Aircraft
• Quality inspection of AAAU components using methods such as visual inspection check,dimensional check and report preparation.
• Material management activities for AAAU components.