Another significant tail configuration

which could be utilized for the glider tail research design is the V-tail which

is characterised with two distinct sections and can be considered similar to

the conventional tail configuration albeit without a vertical tail and a high anhedral

angle. The two individual sections of the V-tail are accountable for the

functions of the horizontal and vertical tails which enables it to perform the

objectives of longitudinal and directional trim. On the contrary, the V-tail

configuration is also considered responsible for inefficiency in monitoring the

directional and longitudinal stability. The slanted tail surfaces are

responsible for providing the functionalities of the elevator and rudder

configuration implemented in a conventional tail. This leads to another

considerable disadvantage in context of the V-tail configuration since the

complexity of the control systems for a glider are increased considerably in

the tail configuration(Gilad Silver, 2014).

The

calculations of the flight test results for the Amethyst Glider can be

presented in the form of four distinct tests which involves collection of data

related to distance and flight time. The basic constants that are implemented

in the case of the flight tests include the total glider weight estimated at

0.15 kg and height from ground as 1.98 m denoted by ‘h’. The flight attempts

are considered invalid according to the BMFA A/2 class F1A rules owing to the

flight time being less than 10 seconds. On the other hand, ignoring the basic

consideration for 10 seconds flight time for calculating the average flight

speed still depicts that the flight attempt would be unsuccessful according to

the 3.1.6.2.c. according to the BMFA Free Flight Rules. The Average Flight

Speed calculated was found to be 5.003 and the improvement of glider’s

performance could be accomplished through installing an aerofoil that can

accomplish higher speeds than 5 m/s. The coefficient of lift was estimated by

considering two constants such as wing span and cord length at 1.245 m and

chord length at 0.104 m. The coefficient was estimated to be 0.1937.