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The Tailless Aircraft

This report on tailless airplane presents the professionals and negative aspects of using this plane design for commercial purposes. The record comprises 4 parts talking about the aerodynamics, structural innovations, motors and overall advantages and disadvantages of tailless plane. The aerodynamic study of your tailless aircraft shows the importance of the influx drag and span loading distribution and different designs that can increase the aerodynamic performance effectively. In structural innovations, several existing tailless aircraft are examined to identify how the buildings have been designed to create an effective aircraft. Specifically, structures used in the control and balance of the aircraft are examined. As regards to engines, the placement of the engine motor and the idea of by using a Vertical Takeoff has been reviewed. The advantages and disadvantages of a tailless airplane have been complete.


Of the aircraft used today, the vast majority use a tailplane to accommodate rudder and elevators. Airplane without such a system remain quite uncommon. However, the concept of tailless aircraft is definitely considered by designers and aviators as an aerodynamically ideal. In the annals of the aircraft design several endeavors were designed to build an aeroplanes with reduced tail size which includes sometimes led to smaller move and weight but has put into controllability problems. Because of this, tailless designs have mostly been used in military applications. In this particular report we evaluate whether it is now possible to seriously use this idea in commercial aeroplanes.


The information within this statement was primarily compiled from books and internet research. Four different facets of the subject were discovered and each aspect was investigated and written up by one member of the group. Also, the group were able to take a look at a harrier jump jet which stopped at Perth on 7th May 2010.

Results of findings

The following stand summarises what the research has unveiled:

Negative points

Lower account and interference drag

Lift to pull ratio raises by 20-25%

Engines can be situated in the centre rear rather than a tail, providing the additional good thing about directional stability

Roll control is more efficient anticipated to large wingspan

The hint of the wing aerofoil is not near to the stall angle due to backward sweep along with twisted wing tip

Vertical takeoff is not useful since a large commercial aircraft weighs too much for the thrust available from current engine unit technology to overcome

Directional control is more challenging to accomplish without adding a rudder assembly

The triangular spanwise aerodynamic loading distribution will not supply the best aerodynamic performance even though the wave pull is the reduced.

Section 1: Aerodynamics

This section of the report talks about the aerodynamics of the tailless aircraft and different factors impacting the same. A tailless a is a cutting edge conceptual change from the classical design that is prevailing for the past 50 years i. e. a wing mounted on a cylindrical fuselage with a tail to guarantee the balance and manoeuvrability of the aircraft.

Lower wetted area (area which is in touch with the external air flow) to quantity percentage and lower disturbance drag is the main aerodynamic advantage of a tailless aeroplanes in comparison to the conventional aircraft.

On the aerodynamic performance aspect, the utmost lift-to-drag ratio depends on the percentage of the plane course to the rectangular root of the product of the induced move factor and the zero-lift drag area, which is proportional to the wetted section of the aircraft.

() potential =

Where Cf is the average friction co-efficient (mainly reliant on the Reynolds quantity) over the wetted area Swet and is also the friction co-efficient.

Since the tailless airplane have a lesser aspect percentage but also a lower friction co-efficient because of its much larger chord, we always get smaller relative wetted area. This gives a considerable improvement in aerodynamic performance by increasing the lift-to-drag ratio of tailless aeroplanes in sail to about 20-25% as compared to the traditional aircrafts.

The BWB-450 and BWB-800 were designed to compare with the existing fleet of conventional aircrafts as Boeing 747 and Airbus 380. BWB-450 was offered the span and the aspect percentage being reduced to 80 m and 7. 55 respectively, in so doing concluding a decrease in 30%fuel burn up per seat for the BWB models as compared to other traditional aircrafts and so requiring 3 instead of 4 machines.

Moreover another such design task was effectively completed, which is based on a similar payload and performance as Airbus 380 with over 650 people. The configuration of the project is perfect for the use of laminar circulation technology (which results in skin area friction drag) to the engine unit Nacelle and probably to the lifting surfaces. Also a rise in cruise trip Mach number increases the drag making the look of airplane unfeasible.

Geometry and stream conditions:

Full-size image (10K) - Opens new window

A thick streamlined centre body where in fact the payload is accommodated to 0-13m span


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