Analysis of Morphing Airfoil Structures and Fabrication of the Wing using the Concept of Additive Manufacturing

This paper briefs about the morphing airfoil with variable camber and it makes use of compliant rib mechanism. Lightweight system for actuation, complaint internal structure and a flexible skin are some of the key requirements for such mechanisms. Wing morphing is a biologically inspired technique where-in, the change in shape of wings can offer various advantages compared to the conventional solutions we currently have. In this research, we have used the combination of materials such as PLA and TPU in the wing prototype that are printed using the concept of additive manufacturing. To meet desirable shape changes, stiffness can either be tailored or actively controlled to guarantee flexibility in the chord-wise (or span-wise) direction with tailored actuation forces. Hence, corrugated structures, segmented structures, reinforced elastomers or flexible matrix composite tubes embedded in a low modulus membrane are all possible structures for morphing skins. Keywords—Complaint rib mechanism, elastomers, flexible skin.

INTRODUCTION It was not until the late 19th Century that the concept of flight took the entire world by awe and surprise, and now it has become one of the most significant commodities that describes economies of several nations. From a recent study, conducted by the International Air Transport Association (IATA), global aviation contributes to $2.7 Trillion (3.6%) of the world's Gross Domestic Product (GDP). Having this big of an impact on the global economy, it is only natural for airlines to set their ultimate goal to profit and/or save their finances out of this. But this procedure of saving finances/economy cannot compromise enhancement in their services. This gap between the Service sector and the economy is only bridged by the quality and performance of the aircrafts that the airlines purchase.
The expected result out of every aircraft that any airline purchases is to transport a large amount of payload, be it passengers and/or cargo, at the least possible expense incurred to the airline itself. A major portion of the expense is occupied by Fuel, followed by airport parking/terminal charges and maintenance/service of aircrafts. This only calls for aircrafts to be manufactured in such a way that it is highly efficient in case of fuel consumption. Thanks to the relentless advancements of technology since the early 20thth century, we, the people of the 21st century, reap the profits of highly fuel efficient aircrafts. Several manufacturers of airframes and propulsion systems, from all around the world have invested their profits into research and development organizations to improve the technology in order to enhance the fuel economy of their respective systems.
Morphing technology on aircraft has grabbed interest over the last decade because it improves the performance and efficiency over a wider range of flight conditions. Morphing wings can also be defined as wings that changes its configuration to maximize its performance at various different flight conditions and purpose. Morphing aircraft wings have requirements such as flexible skins that can undergo large strains and have low in-plane stiffness. For example, a radical change in configuration, i.e. wing geometry in flight may improve overall flight performance during take-off, cruise and landing.

A. Airfoil Selection
Selig1223 from the Selig series, FX74MODSM from the WORTMAN series and Eppler 423 from the Eppler series of airfoils were shortlisted. Originating from the Low Speed and Low Reynolds number regime, these airfoils were analyzed and selected by means of reference scoring method.
The parameters considered were Clmax, Cdmin, Stall angle, Cl/Cd and ease of fabrication. The airfoil with the most favourable outcome of the listed parameters would be scored a maximum of 3 and the airfoil with the least favourable outcome would be scored a minimum of 1.

International Journal of Engineering Research & Technology (IJERT)
ISSN: 2278-0181 http://www.ijert.org The airfoil characteristic plots such as Cl vs. AOA, Cl vs. Cd, Cm vs. AOA and (Cl/Cd) vs. AOA at Re= 500,000 were studied and the reference scoring method was employed to choose the best out of all three airfoils. The plot above shows the Lift coefficient trend with respect to angle of attack. We further observe that S1223 has the best stall performance followed by E423. But we also observe that FX74modsm has the highest lift coefficient. The plot above shows us the variation of lift coefficient with respect to drag coefficient. We further observe that E423 has the least drag coefficient followed by FX74modsm. We also observe that the S1223 has the highest drag coefficient value out of all the three airfoils. Hence we give E423 the highest score of 3 followed by 2 for FX74modsm and the least favourable score of 1 to S1223. The figure 3 shows the variation of aerodynamic efficiency, that is the ratio of Cl to Cd versus angle of attack. We observe that the E423 has the highest Cl to Cd ratio at approximately 5º followed by FX74modsm and then the S1223 has the least Cl to Cd ratio relative to the other two. Hence, E423 gets the highest score of 3 and S1223 gets the least score of 1.
The table below is the integral representation of the reference scoring methodology employed to choose one Airfoil. The scores for individual parameters are distributed and then the Airfoil's total score is computed.

B. Airfoil Selection
The primary task, to be able to define any analysis was to figure out a method to modify the E423 airfoil. It is a highly tedious task to be changing the co-ordinates of the airfoil empirically to replicate a morphed trailing edge. To avoid this, we imported the airfoil co-ordinates into CATIA Generative Shape Design. The airfoil profile was extruded to form a surface. This airfoil surface was deformed to imitate a control surface deflection by using the SHAPE MORPHING tool. And once the surface was morphed, a 2-D profile of the morphed airfoil was projected. This morphed airfoil profile was used to create a 2-D surface which was then imported into the ANSYS Workbench. The airfoil surface was saved in .igs format and was then imported into ANSYS Fluent. The Geometry of a test section was sketched and the airfoil surface was removed to create the impression of the airfoil cavity using Boolean tool.  The morphed airfoil was analyzed and the pressure and velocity contours were obtained along with the lift and drag coefficients. The above steps were repeated with a hinged airfoil and the corresponding results were obtained. The table below shows us the lift and drag coefficients along with the aerodynamic efficiency of morphed and hinged airfoil profiles.

A. Designing the Prototype
The goal was to keep the monolithic structure as the rib design and a strong leading edge region. The resulting design was generated as shown below. • The product was converted to ".iges" format and imported into Ansys Work bench static Structural Geometry Window.
• The mechanical properties of the materials used was saved at the Engineering Data tab as follows. • The saved material data was assigned to their respective parts.
• The model was meshed and refined to the second order. This was done to increase the number of nodes thereby facilitating an accurate result. The Inner Core Element, 3D printed out of PLA, was to be covered using a flexible skin which also shares the same profile as that of the chosen airfoil. This Skin was 3D printed using TPU filament and was done to keep a smooth surface exposed to the air (fluid). The following figure represents what the skin will look like.

B. Structural Analysis
A structural analysis was conducted and the steps mentioned below were followed.
• Engineering Data was updated with mechanical properties of PLA filament and the Inner core was imported into geometry window. • This was further meshed and the analysis settings were updated as follows. • The entire truss leading edge region was identified as a fixed support and a force of 100N was applied at the control horn in the pulling direction which makes the control surface deflect down. • The figure below shows the location of the fixed support and the location where the load is applied and also the direction of the load.  IV. MORPHED WING PROTOTYPE For our final prototype model we have used the 3-D printing method. 3-D printing is often referred to as the additive manufacturing of which we have used materials like PLA for the main structure of the wing and TPU for the skin. These two materials, when used together, are very flexible and tougher. V. RESULTS AND DISCUSSIONS The mechanism was tested and proven for enhancing aerodynamic as well as structural efficiency. The design was fabricated and the structural analysis was experimentally verified.
The following results were observed during the experimental testing of the assembly after 3D printing the model. As and when the duration of run time of the Inner Core was increased, it was observed that there was a slight increase in the deflection values. This experimental test was conducted in a rather primitive arrangement and helped us empirically determine the maximum number of times it would be safe to operate this compliant mechanism. It was determined that any more number of cycles after the 300 mark would result in a partial structural failure, therefore considering a FOS of 0.5, it was empirically established that 150 cycles within a time frame of 800s was the optimum number of cycles.

ACKNOWLEDGMENT
We thank the writers whose research papers we referred and developed the baseline for our research work, which we were able to change and deliver good results according to our requirements. Our mentor, Dr. R Rajendran, we are grateful to him for his helpful feedback. We extend our gratitude to Flexfoil (by FlexSys Inc.) for the inspiration. The variable surface controls of FlexFoil, geometrically reflect a major change over traditional aircraft flaps. The FlexFoil control surface adjusts wing cambers as they are moving rather than utilizing the heavy and bulky system of the regular wing assemblies, by leveraging the inherent elasticity of aviation grade materials.