AERONAUTICAL ENGINEERING
Project HIGHLIGHTS

Foot Step Energy Harvester - IEDC Sponsored Project

Students of the 6th Semester, Niraj Panthi, Ebin Baby, have successfully completed an Innovation and Entrepreneur Development Cell (IEDC), NMIT, sponsored project titled, " Foot Step Energy Harvester", using piezoelectric transducer under the guidance of Mr. Santhosh Nagaraja, Assistant Professor, Department of Aeronautical Engineering.

Development of Asymmetric Flapping Mechanism for Flapping Wing MAV

Students: Niraj Panthi, Ebin Baby and Sowmya Nagaraj (8th Sem, 2011-12 Batch)

Guides: Dr. Parag Deshpande (MAV Unit, NAL) and Dr. Shaik Ismail (Aero Engg, NMIT)

This project deals with the design, fabrication and aerodynamic analysis, including Wind Tunnel testing, of an asymmetrical flapping mechanism for a flapping wing MAV. Crank and slotted lever quick return mechanism is used to develop the asymmetric flapping wing MAV which results in time difference in upstroke and downstroke motion leading to the net positive lift even at zero angle of attack. The project was carried out at the MART (Micro Air Vehicle Research Wind Tunnel) of NAL.

An elliptical wing plan form was selected for the MAV. An experimental study was carried out to assess the effectiveness of asymmetrical flapping for a frequency range of 3 Hz to 12 Hz, and over varying time ratios from 1.58 to 3.05. The physical model was fabricated using 3D printing technique, and tested in normal atmospheric conditions and in a Low Speed Wind Tunnel in the velocity range of 2 to 4 m/s. The effect of advance ratio on the coefficient of thrust and the coefficient of lift was studied. Visualization of flow was done using a green laser beam incident on mid span of the wing. It was concluded that flapping flight would bring significant aerodynamic benefits, that is, generate much more lift and thrust if the flapping flight is in unsteady state regime with the advance ratio less than unity.

   
3D Model of Asymmetric Flapping Mechanism (using Solid Works)   3D Fabricated Model mounted in Wind Tunnel  
   
 
Flow Visualization in Wind Tunnel  
Experimental Investigation of Boundary Layer Control over Airfoil through Momentum Injection by Moving Surface at Low Reynolds Numbers

Students: Anuj Gupta and Samak Manjushree (8th Sem, 2011-12 Batch)

Guides: Dr. Parag Deshpande (MAV Unit, NAL) and Dr. Shaik Ismail (Aero Engg, NMIT)

The main aim of the project is to control the boundary layer over an airfoil using active technique to delay separation and stall, and to essentially reduce profile drag by increasing the momentum of flow over the surface by employing a rotating cylinder at the leading edge of the airfoil. The project was carried out at the MAV Unit of NAL.

A foam model of NACA 4415 airfoil with a chord length of 120 mm, and a span of 190 mm was fabricated with pressure tappings on the surface and a rotating cylinder at the leading edge. The airfoil model was mounted in a Wind Tunnel section of 200mmX200mm, and Cp measurements were carried out and tabulated. Also, a wake survey was done on RPT model of same configuration, and flow visualization was carried out.

NACA 4415 airfoil with a rotating cylinder at LE Baseline flow pattern (no rotating cylinder)
   
 
Flow pattern with rotating cylinder at LE  
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