Abstract:
To improve the overall lift to drag a new concept on fuselage of an Unmanned Aerial
Vehicle (UAV) is investigated where the fuselage also provides some lift. To
investigate the improvement of lift to drag two fuselages are considered, one is
conventional cylindrical cross-section and the other is aerofoil cross-section. A
number of fuselages models with a scale of I :32 with aerofoil cross-section and with
conventional cylindrical cross section are manufactured in such a way that both
models have the same volume. Same set of wings is used in both types of models so
that the results can be used to show the comparison between the fuselages. To reduce
the induced drag winglets are used in aerofoiled fuselage. All the three fuselages i.e.,
circular cross-sectioned, aerofoil cross-sectioned and aerofoil cross-sectioned with
winglets are used for wind tunnel test. Lifts and drags are measured with the help of
spring balance system for different angle of attack of the fuselages to find out the best
fuselage corresponding to overall lift to drag ratio. From this result it is also found out
what should be the best angle of attack of the fuselage at different speed during take
off, flying and landing condition. Finally lifts and drags are also measured by pressure
tapping around the fuselages at different angles of attack to verify the results found in
spring balance system.
