Equations

Lift

½ Rho V² S Cl

Profile Drag

½ Rho V² S Cd

Dynamic Pressure

½ Rho V²

Induced Drag

Cl² / Pi Ar

Load Factor

Lift / Weight

Load Factor in a turn

1 / Cos(AoB)

Stalling speed with Weight Change

Vs(New Weight) = Vs (Old Weight) √(new weight / old weight)

Stalling Speed with Bank Angle change

Vs (New AoB) = Vs (old AoB) √(Cos(Old AoB)/Cos(New AoB))

Stalling speed and Load Factor

Vs(n) = Vs(1g) √n

Design Manoeuvre Speed

Va = Vs(1g) √(limiting n)

Changes in Va with Weight Change

Va (New Weight) = Va (Old Weight) √(new weight / old weight)

Changes with Va with Cl Change

Va (New) = Va (Old) √(Cl (Old) / Cl (New))

Gust Load Factor

New Cl in Gust / Cl Before Gust

Radius of a turn

V² / g Tan(AoB)

Rate of Turn

g Tan(AoB) / V (in Radians)

Steep Climb Gradient Drag

T - Wsin(+-y)

Steep Climb Gradient Lift

Wcos(+-y)

Shallow Climb Angle

Sin(y) = T/W - Cd/Cl

Angle Of Climb

Tan(y) = (Height Gained / Distance Gone)

Mach Angle

Sin(A) = 1/Mach Number

Mach Number

TAS / LSS

Local Speed Sound

39 √Kelvin

Wing Loading

Weight / Area

Taper Ratio

Chord Tip / Chord Root

Aspect Ratio

Span / Average Chord OR Span² / Area

Average Chord

Wing Area / Span

Combined gas laws

PV / T = Constant

Stalling speed

√(2W / p S Clmax)

Weight in a turn

Lcos(AoB)