Author name: Akash Babu S L

The Lift for Rotating Wings accounts for the lift generated by a rotating wing or rotor, such as those used in helicopters   L is the lift force, ρ is the air density, A is the disc area, Ω is the angular velocity of the rotor, r is the radius from the center of rotation […]

The Kutta-Joukowski Theorem states that the lift force on an airfoil is proportional to the air density (ρ), the freestream velocity (V), and the circulation (Γ) around the airfoil.   L is the lift force, ρ is the air density, V is the freestream velocity, and Γ is the circulation around the airfoil.

Circulation (Γ) is a measure of the circulation of the air around an airfoil   Γ is the circulation, ρ is the air density, and Vcirc​ is the circulation velocity.

The Aerodynamic Heating Equation is used to calculate the heat flux experienced by a reentering spacecraft or object moving through a fluid medium, typically the Earth’s atmosphere.   q is the heat flux, ρ is the atmospheric density, V is the velocity of the object relative to the atmosphere, CL​ is the lift coefficient.

The Orbital Energy Equation is an expression used in celestial mechanics to describe the total mechanical energy of an object in orbit   E is the total orbital energy, G is the gravitational constant M is the mass of the central body m is the mass of the object in orbit, a is the semi-major

Specific Gas Constant for Aircraft Design (R) is defined as the ratio of the universal gas constant (Ru​) to the molar mass (M) of the gas   R is the specific gas constant, Ru​ is the universal gas constant (8.314 J/(mol \cdotK) M is the molar mass of the gas.

The Standard Atmosphere Lapse Rate describes the temperature variation with altitude in the standard atmosphere   T is the temperature at altitude ℎh, T0​ is the sea-level temperature, L is the lapse rate (temperature decrease per unit increase in altitude), ℎ is the altitude

The Oswald Efficiency Factor (e) is a dimensionless parameter used in aerodynamics to characterize the efficiency of an aircraft’s wing in generating lift   e is the Oswald Efficiency Factor. π is the mathematical constant pi (approximately 3.14159). A is the aspect ratio of the wing. AR is the aspect ratio, defined as the square

The Center of Gravity Range (C GR​) is a parameter that characterizes the allowable variation in the longitudinal position of the center of gravity (CG) for an aircraft   CGR​ is the Center of Gravity Range. xCG max​​ is the maximum longitudinal position of the center of gravity. xCG min​​ is the minimum longitudinal position

The Vertical Tail Volume Coefficient (Vvt​) is a dimensionless parameter used in aircraft stability and control analysis.   Vvt​ is the Vertical Tail Volume Coefficient. Svt​ is the vertical tail area. lvt​ is the distance from the aircraft centerline to the center of the vertical tail. S is the reference area, typically the wing area.