By providing the improvement rates in L/D, this paper numerically evaluates and validates the efficiency of camber morphing aircraft, the most important aspect of aircraft operation, as well as the agility and manoeuvrability, compared to conventional wing aircraft. Overall, in the entire range of α, which conceptualizes aircrafts mission planning for operation, camber morphing wings are superior in D, L/D, and their improvement rate over conventional ones. As a result, we validate that variable camber morphing wings, equivalent to conventional wings with varying flap deflection angles, are improved by at least 1.7% in their L/D ratio, and up to 18.7% in their angle of attack, with α = 8° at a 3% camber morphing rate. Finally, we find matching pairs for a direct comparison to validate the effectiveness of morphing wings.
#Camber airfoil verification#
All things considered, this paper starts with the verification of the numerical model used for the aerodynamic performance analysis and then conducts the aerodynamic performance analysis of (1) variable camber rate in morphing wings and (2) variable deflection angles in conventional wings. However, the foundational work that establishes the motivation of morphing technology development has been overlooked in most research works. Many morphing-related research works mainly focus on the design of morphing mechanisms using smart materials, and innovative mechanism designs through materials and structure advancements. Cambered airfoils are also used in a propeller blade.This paper aims to numerically validate the aerodynamic performance and benefits of variable camber rate morphing wings, by comparing them to conventional ones with plain flaps, when deflection angles vary, assessing their D reduction or L/D improvement. Aircraft designers can vary the camber along the wing span to give different lift characteristics which may be used to improve stall condition or stall recovery. Therefore, all aircraft generally uses an cambered airfoil. Cambered airfoil produces more lift and less drag than a symmetrical airfoil, given at the same density, airspeed, and angle of attack. Aerodynamic center and center of pressure does not lie at the same point in a cambered airfoil. A cambered airfoil can produce lift even at zero degree angle of attack in an airflow. An airfoil having a positive camber is more convex.
Generally, an airfoil has a positive camber which means the mean camber line is above the chord line. An airfoil can have a positive camber or a negative camber. For a cambered airfoil, the mean camber line and the chord line is different. Camber of an airfoil is a measure of airfoil curvature. Horizontal and vertical tails of an aircraft have a symmetric airfoil.Īsymmetric airfoil / Cambered airfoil : An airfoil which has a camber is called an asymmetric or a cambered airfoil. Aerobatic aircraft need to generate lift in spinning or when the aircraft is flying inverted. Symmetric airfoils are used in helicopter rotors and in the wings of an aerobatic aircraft. Also, the aerodynamic center and center of pressure lies at the same point on the airfoil. A symmetric airfoil in an airflow at zero degree angle of attack does not produce any lift. Hence, camber of a symmetric airfoil will be zero. So, the mean camber line and chord line of a symmetric airfoil will be the same. Mean camber line of an airfoil is the line that is halfway between the upper surface and lower surface of the airfoil. A symmetric airfoil has same shape on both sides of the centerline which is chord.
Symmetric airfoil : An airfoil is a cross-sectional shape of a wing.
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