12.62.4(a) . maximum angle of climb;
Maximum angle climb
– best gradient
Maximum rate climb
– best vertical speed
Normal climb
– speed is usually higher than the speed for maximum rate of climb and is a compromise between speed and rate of climb
Vx max angle
Vy max rate
12.62.4. Distinguish between:
12.62.2. Using a diagram, show and name the forces acting in a steady climb.
++ Diagram++
The aerodynamic lift force acts perpendicular to the direction of flight
The drag force is parallel with it
Weight force acts vertically downwards but in the climb it now has a component which acts in the same direction as drag
12.60. Straight and Level Flight
12.60.10. Explain the basic operational considerations which apply to flying an aeroplanefor range, or endurance.
Range
– if headwind not a factor tend toward flying at higher altitudes – “cruise climb”
– ensure the mixture is properly leaned
– fly at an altitude that reduces the headwind component to a minimum or an altritude that takes advantage of a higher tailwind component
Endurance:
– fly at about the recommended gliding speed
– in turbulent conditins fly at a slightly higher speed to prevent large increases in power to overcome effects of gusts
– ensure the mixture is correctly leaned
– fly at the lowest practical attitude
12.60.8(c) . maximum endurance speed.
Speed for maximum endurance is the TAS which coincides with the bottom of the power curve – ie the speed at which the minimum power and lowest fuel consumption is required to maintian level flight
12.60.8(b) . maximum-range speed;
Maximum range is achieved in level flight where the greatest distance is covered for the least amount of fuel
The maximum range is the TAS at which the line drawn from the origin of the graph is tangential to the bottom of the power curve
12.60.8(a) . maximum and minimum level flight speed;
Maximum level flight speed
– where power available and power required lines cross at higher TAS true airspeed
Minimum level flight speed
– this is where the power availbale and power required lines cross at the lower TAS – where
12.60.8. Given a basic graph of power available (PA) and power required (PR) versus TASin level flight, show the derivation of:
12.60.6. Describe the pitching moments in flight, and how longitudinal stability isachieved.