Vaimanika Shastra

AIRFOIL TERMINOLOGY

Air foil Terminology What is an airfoil? How an air foil is described in modern science, what are the parameters that determines its shape? An Air foil is primary building block of an aircraft which has two edges namely leading edge and trailing edge, the straight line connecting the leading and trailing edge of the air foil is called as chord line. The line which is drawn equidistant from the upper and lower surfaces of the air foil and connecting the leading and trailing edge is called as mean camber line.The distance between the leading and trailing edge is called chord of an air foil. The maximum distance between the mean camber line and chord line is referred as maximum camber. This is one of the variables that determine the aerodynamic characteristics of the wings. Maximum thickness to chord ratio is expressed in terms of percentage. For subsonic wings the ratio is normally 12-14%...

Form Drag

Form Drag Form drag is experienced in the surface of the aircraft when the streamlined airflow separates and becomes turbulent. To experiment form drag keep a flat plate on the streamlined airflow, now the pressure before the plate is atmospheric and the pressure after it is below the atmospheric which results in sucking effect behind the plate and vortices are formed. It is mandatory to delay the separation point of airflow and this is achieved by altering the shape or streamline of the given object. When the airflow changes its direction rapidly form drag experienced is higher. A fairing is fitted around the fixed undercarriage leg to reduce form drag to consi...

Coefficient of Lift

Lift Coefficient: Coefficient of lift C L is defined as the lifting ability of the wing which depends on geometry of the airfoil. Coefficient of Lift Changes with change in angle of attack and it differs for symmetric and Assymetric airfoils. To Know about Coefficient of lift C L we plot the variation of lift with change in angle of attack. For asymmetric airfoil at 0 degree of angle of attack the lift generated is minimum and at 15-16 degrees its maximum which is called C L max . Angle of attack remains a straight line between 0 -12 Degrees. Above 12 Degrees rate of increase in lift reduces and forms a peak. The Peak formed denotes the maximum A...

AEROFORUM

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