Presenters

Kyle MelloFollow

Academic department under which the project should be listed

SPCEET - Mechanical Engineering

Faculty Sponsor Name

Dr. Cameron Coates

Abstract (300 words maximum)

The goal of this project is to conceptually design a lift system consisting of rotating cylinders that may improve certain flight characteristics when compared to conventional wings for a typical two passenger airplane. The functions of flaps, ailerons, lift to weight ratio and structural responses are considered. The cylindrical model is developed within CFD simulation software such that it generates the same lift produced by the wings of a Cessna 172 wings at cruising speed. Incompressible flow theoretical solutions are initially shown to compare favorably with the computational predictions for elementary cylindrical designs.

The rotating cylinder aircraft generates the same lift as a Cessna 172 flying at 40m/s at an angle of attack of 2.5 degrees. Theoretical calculations and CFD simulation both show the rotating cylinders to generate a lift to weight ratio of 27.2, compared to the Cessna’s 7.58. The main concern of this dynamic lift system is its structural integrity under constant rotation. At rotational speeds up to 350rad/s, the cylinders are well within their structural limits of resisting hoop and shear stresses.

A dual shaft electric motor is used to power the cylinders to generate lift. The ailerons are replaced by using eddy current brakes to slow down the rotational speed of one of the cylinders, causing the aircraft to roll. The flaps are replaced by simply increasing the rotational speed of the cylinders.

Project Type

Event

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Lifting Flow over a Cylinder as a Lift System

The goal of this project is to conceptually design a lift system consisting of rotating cylinders that may improve certain flight characteristics when compared to conventional wings for a typical two passenger airplane. The functions of flaps, ailerons, lift to weight ratio and structural responses are considered. The cylindrical model is developed within CFD simulation software such that it generates the same lift produced by the wings of a Cessna 172 wings at cruising speed. Incompressible flow theoretical solutions are initially shown to compare favorably with the computational predictions for elementary cylindrical designs.

The rotating cylinder aircraft generates the same lift as a Cessna 172 flying at 40m/s at an angle of attack of 2.5 degrees. Theoretical calculations and CFD simulation both show the rotating cylinders to generate a lift to weight ratio of 27.2, compared to the Cessna’s 7.58. The main concern of this dynamic lift system is its structural integrity under constant rotation. At rotational speeds up to 350rad/s, the cylinders are well within their structural limits of resisting hoop and shear stresses.

A dual shaft electric motor is used to power the cylinders to generate lift. The ailerons are replaced by using eddy current brakes to slow down the rotational speed of one of the cylinders, causing the aircraft to roll. The flaps are replaced by simply increasing the rotational speed of the cylinders.