Author name: Akash Babu S L

Vertical wind shear refers to the change in wind speed and direction along the vertical axis within the jet stream.   ΔV is the change in vertical wind speed. Δz is the vertical distance over which the change occurs. [CP_CALCULATED_FIELDS id=”3353″

Horizontal Wind Shear refers to the change in wind speed and direction along the horizontal within the jet stream ΔV is the change in horizontal wind speed. Δx is the horizontal distance over which the change occurs.

The Flap Effectiveness Factor (Kf​) is a parameter used in aircraft design to quantify the effectiveness of flaps in increasing the lift of an aircraft.   Kf​ is the Flap Effectiveness Factor. ΔCL​ is the change in lift coefficient due to the deployment of flaps. δf​ is the deflection angle of the flaps.

The damping ratio (ζ) in control system response is a dimensionless parameter that characterizes the rate of decay of oscillations in a system.   Real part of complex pole is the part of the pole that isn’tassociated with the imaginary unit Magnitude of Complex Poles is the distance of the pole from the origin in

The Inlet Mach Number (M inlet​) for air intakes is a parameter used in the design and analysis of aircraft engines, particularly inlets that bring air into the propulsion system   M inlet​ is the Inlet Mach Number, V inlet​ is the velocity of the incoming air at the inlet, and a inlet​ is the

The specific heat ratio (γ) is the ratio of the amount of heat required to raise the temperature of a substance at constant pressure to the amount of heat required to raise the temperature of the same substance at constant volume.   Cp​ is the specific heat at constant pressure, Cv​ is the specific heat

Nondimensional Thrust-Specific Fuel Consumption (TSFCTSFC) represents the amount of fuel an aircraft engine consumes to produce a unit of thrust   TSFC is the nondimensional thrust-specific fuel consumption, m˙fuel​ is the fuel flow rate, T is the thrust.

Fuselage Drag Coefficient (CDf​​) quantifies the drag contribution of the fuselage to the total drag of an aircraft.   CDf​​ is the fuselage drag coefficient, S wet​ is the wetted area of the fuselage, S is the wing reference area.

The time constant (τ) is calculated as the reciprocal of the product of the damping ratio (ζ) and the natural frequency (ωn​). Time Constant (τ) Damping Ratio (ζ) Natural Frequency (ωn​)

The lift slope (a) is the rate of change of the lift coefficient (CL​) with respect to the angle of attack (α). Lift Coefficient (CL​) Angle of Attack (α) Lift Slope (a)