Ch 19 - Level Flight And Climb Flashcards
Pitch Angle
AoA + Flight Path Angle
AoA
The angle between the flight path angle and the longitudinal axis
Flight Path Angle
The angle between the Horizontal axis and the Relative airflow
Load Force
= Lift / Weight
Lift equation in a steady climb
L = W cos Gamma
Flight Path Angle Equation
Sin Gamma = (Thrust - Drag) / Weight
Vx
Climbing angle
Will increase with a heavier aircraft
Will decrease with a dirty configuration
Turbojet = Greatest excess thrust which is the same as Vmd
- Close to stall speed
Effect of Altitude on Flight Path
thrust decreases with altitude so the climb angle has to reduce. So as you climb you end to continually decrease the pitch to maintain a constant AoA
Climb Gradient Equation
%G = (T-D)/W X100