Lec11 - nptel
... In general, when aircraft is being referred to be in stable equilibrium, we mean dynamic stability. However, it so happen that for most of the cases, for conventional aircraft, if it is statically stable, it also automatically satisfies dynamic stability criterion – but not all aircraft! Handling qu ...
... In general, when aircraft is being referred to be in stable equilibrium, we mean dynamic stability. However, it so happen that for most of the cases, for conventional aircraft, if it is statically stable, it also automatically satisfies dynamic stability criterion – but not all aircraft! Handling qu ...
Forces on an Airplane in Flight
... Since lift is dependant on the motion of the air, it increases as the speed of the air increases. Lift also increases (to a point) as the angle that the wing makes with the airflow (known as the angle of attack) increases. Past a certain point, however, increased angle of attack will cause the wing ...
... Since lift is dependant on the motion of the air, it increases as the speed of the air increases. Lift also increases (to a point) as the angle that the wing makes with the airflow (known as the angle of attack) increases. Past a certain point, however, increased angle of attack will cause the wing ...
Velocity
... Terminal Velocity • When a sky diver leaves the aircraft he speeds up because there are unbalanced forces acting. His weight is greater than the fictional drag force. • As his speed increases, the fictional drag due to the air increases. • Spreading himself like a eagle increases the surface area a ...
... Terminal Velocity • When a sky diver leaves the aircraft he speeds up because there are unbalanced forces acting. His weight is greater than the fictional drag force. • As his speed increases, the fictional drag due to the air increases. • Spreading himself like a eagle increases the surface area a ...
Word
... where CL is the lift coefficient, CL = 2FL /(V2A); A is the airfoil’s planform area, A = sc; Rec is the Reynolds number based on chord length, Re = Vc/; and Ma is the Mach number, Ma = V/a. Note that since area A has the same dimensions {L2} as does c2, we have also substituted A for c2 in the li ...
... where CL is the lift coefficient, CL = 2FL /(V2A); A is the airfoil’s planform area, A = sc; Rec is the Reynolds number based on chord length, Re = Vc/; and Ma is the Mach number, Ma = V/a. Note that since area A has the same dimensions {L2} as does c2, we have also substituted A for c2 in the li ...
4.2.1.A-FourForcesofFlight
... • The direction of the thrust force depends on how the engines are attached to the aircraft. • When engines are located under the wings, parallel to the body, thrust acts along the body centerline. ...
... • The direction of the thrust force depends on how the engines are attached to the aircraft. • When engines are located under the wings, parallel to the body, thrust acts along the body centerline. ...
Flight dynamics (fixed-wing aircraft)
Flight dynamics is the science of air vehicle orientation and control in three dimensions. The three critical flight dynamics parameters are the angles of rotation in three dimensions about the vehicle's center of mass, known as pitch, roll and yaw.Aerospace engineers develop control systems for a vehicle's orientation (attitude) about its center of mass. The control systems include actuators, which exert forces in various directions, and generate rotational forces or moments about the aerodynamic center of the aircraft, and thus rotate the aircraft in pitch, roll, or yaw. For example, a pitching moment is a vertical force applied at a distance forward or aft from the aerodynamic center of the aircraft, causing the aircraft to pitch up or down.Roll, pitch and yaw refer to rotations about the respective axes starting from a defined steady flight equilibrium state. The equilibrium roll angle is known as wings level or zero bank angle, equivalent to a level heeling angle on a ship. Yaw is known as ""heading"". The equilibrium pitch angle in submarine and airship parlance is known as ""trim"", but in aircraft, this usually refers to angle of attack, rather than orientation. However, common usage ignores this distinction between equilibrium and dynamic cases.The most common aeronautical convention defines the roll as acting about the longitudinal axis, positive with the starboard (right) wing down. The yaw is about the vertical body axis, positive with the nose to starboard. Pitch is about an axis perpendicular to the longitudinal plane of symmetry, positive nose up.A fixed-wing aircraft increases or decreases the lift generated by the wings when it pitches nose up or down by increasing or decreasing the angle of attack (AOA). The roll angle is also known as bank angle on a fixed-wing aircraft, which usually ""banks"" to change the horizontal direction of flight. An aircraft is usually streamlined from nose to tail to reduce drag making it typically advantageous to keep the sideslip angle near zero, though there are instances when an aircraft may be deliberately ""sideslipped"" for example a slip in a fixed-wing aircraft.