• G. Manjula
• L. BALASUBRAMANYAM
• S. JITHENDRA NAIK

Disc rotor configuration may be a conceptual design. the aim of the Project is to guage the merits of the DiscRotor concept that combine the features of a retractable rotor system for vertical take-off and landing (VTOL) with an integral, circular wing for high-speed flight. The primary objective of this project is to style such a configuration using the planning software Unigraphics and afterward analyzing the designed structure for its structural strength in analysis software ANSYS. This project deals with the all the required aerodynamic requirements of the rotor configuration. In today’s world most the vtol/stol largely depends upon the thrust vectoring that needs huge amounts of fuel and separate devices like nozzles etc., whose production is extremely much tedious and dear. this is often an effort to use a rotor as within the case of helicopters for vtol/stol thus reducing the foremost of the value though weight would be considered as a hindrance to the project.

Disc rotor wing, vertical take-off and landing (VTOL), UNIGRAPHICS, ANSYS software, Force, Coefficients, Wall and Wing.

"MODELING AND ANALYSIS OF DISC ROTOR WING", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.7, Issue 3, page no.161-171, March-2020, Available :http://www.jetir.org/papers/JETIR2003030.pdf

"MODELING AND ANALYSIS OF DISC ROTOR WING", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.7, Issue 3, page no. pp161-171, March-2020, Available at : http://www.jetir.org/papers/JETIR2003030.pdf