Aircraft wing design - Assignment Example

Aircraft wing design Introduction Aircraft design is one of the fundamental engineering areas that has been accorded high importance and concern of the years. design ranging from the smallest element to the aero-plane itself is subjected to extreme research and incorporates a number of design consideration if success is to be achieved. Aircraft wing plays a vital role in its final operation and as such incorporates a number of fundamental design considerations. According to Kundu et al. (2003, p.241). it literally impossible for one to design an aircraft part without comprehensively understanding the role of that part in the aircraft and the fundamental theories that accompany its design. In this paper, a detailed plan for design of an aircraft wing is described on that basis, an aircraft wing model proposed. Design considerations Various design considerations are put into consideration when designing an aircraft wing. these are below: Mechanical considerations These are a very important to consider in designing an appropriate aircraft wing. Span and wing area: The wing span is crucial in design. Basically, this is constrained by the size of the hangar, as well as the ground facilities. However, such must be based on the structural dynamic constraints. Measures must be put in place to minimize the induced direct drag. Consideration is also taken not to raise the wing’s structural weight in a manner that extremely increases the savings on induced drag. the area of the wing, just like is the case in selecting the span considers various aspects include the drag constraint, speed of stalling and field length, as well as the volume of fuel. despite the fact that in some instances these factors allow for creation of small wings, the size of the wing in this case is increased in order to obtain a reasonably appropriate CL on basis of the pre-defined flight conditions (Moir & Seabridge, 2007; Raymer, 2008, p. 67). Sweep Also regularly considered is the sweep. The wing sweep is largely selected on basis of the desirable effect in relation to the transonic wave drag. This allows for larger thickness or even CL at a specified Mach number without resulting into drag divergence. Thickness The thickness distribution from the wing root towards the tip is selected based on the following considerations: 1. The t/c ratio should be as large as can be possible achieved in order to lower the weight of the wing and hence allow a large span. with a larger the CLmax is bound to increase to a given point based on the high lift system (McMasters, 1994). 2. A large t/c volume is also set to give increased volume of fuel and stiffness of the wing. 3. Raising t/c slightly raises the drag through raised velocities as well as the pressure gradients adversity (Nicolai, 2009, p.121). aspect ratio, AR is given by  Wing taper ratio This design aspect will be determined on basis of the following consideration: 1. The plan-form shape must not result into increased lift distribution that is away from the elliptical for necessary twist lower drag results. 2. distribution of the chord should large in a manner that with lift distribution, the lift co-efficient distribution is compatible to the sectional performance. High Cl is avoided to ensure drag remains minimal. 3. the low taper ratio is also meant to ensure the wing’s weight remains low and allows raised volume of fuel. 4. Basically, the design aims to keep the taper ratio as low as possible without resulting into large Cl variation. Twist Although less controversial, it should be selected such that resulting drag is not in excess. It however, alters the wing structural weight by modification of the distribution moment across the aircraft wings. twist is calculated as shown below: Design parameters Based on the design consideration highlighted, the design parameters are therefore chosen as follows: wing span, b = 2.365 m Root code length, lr = 0.255 m tip chord length, lt = 0.175 m sweep angle at c/4 line, j0.25 = 20° lift coefficient design, CL = 0.5 root section, E 180 cm,r = +0.01   and    a0,r = -0.3°  tip section E 184 cm,t = +0.03   and   a0,t = 0.5°  Desirable stability coefficient, sigma = 0.05 The area of the wing, S is therefore calculated and established as shown below: and the aspect ratio and the mean moment coefficient Based on the parameters highlighted, *req = 12°. This is to be corrected to match the design’s coefficient of lift as well as the desirable margin of stability whereby, This implies that model’s angle of twist is 2.95° (wash out) measured from the root’s to tip, when a symmetrical airfoil section is made use of. The variation of the zero lift tip angle and section of the root is given as follows: Based on this, the twist contribution with regard to the moment coefficient that requires correction given as follows:  The geometric twist is calculated as shown: Based on the parameters considered, a final model is developed as shown in the sketch below: It is important to note that design is structured on basis of the calculated parameters in order to ensure that the target aircraft is able to not only meet the standard parameter restrictions but also able to offer maximum efficiency and functionality. Additionally, the wing is targeted to offer maximal limited weight and enhanced fuel volume. This similarly facility maximum capability and functionality, requirements which are key to design of any good aircraft wings. although the wing is not subjected to extensive material selection process, the conventionally used aluminum is preferred for the design in order to ensure the earlier mentioned parameters are successfully achieved (Murman, Walton, & Rebentisch, 2008, p. 248). Generally, the design aims to produce an efficient wing design suitable for a light aircraft. References Kundu, A. K. et al. (2003). Aircraft Component Manufacture Case Studies and Operating Cost Reduction Benefit. AIAA Conference ATIO; Denver. Mattingly, J. D. et al. (2009). Aircraft Engine Design, AIAA Education Series. McMasters, J. H. (1994). Boeing Commercial Aircraft. General Engineering Division, Summer Intern Training Program. Moir, I. & Seabridge, A. (2007). Civil Avionics Systems. Wiley; Chichester Murman, E., Walton, M., & Rebentisch, E. (2008). Challenges in the Better, Faster, Cheaper Era of Aeronautical Design, Engineering and Manufacturing. The Aeronautical Journal, 42 (4), 246 -252. Nicolai, L. M. (2009). Fundamentals of Aircraft Design, METS, Inc., San Jose, California. Raymer, D. P. (2008). Aircraft Design: A Conceptual Approach. AIAA Education Series. Read More