modified Jan, 07, 2006, 22:01 by Charles W. Barbour II
Modifications: - got rid of scratch work
The stall speed of the Aircraft in normal level flight. (Lift=Weight)
straight and level flight alpha as a function of the aircraft's weight and the velocity
Thrust at Sea Level and 1000 ft
Drag at Design Weight +/- 10 lbs.
straight and level flight determined arbitrarily between V_LO and V_max at an angle of attack that gives the largest L/D value.
Rolling Friction Coefficient
The lift coefficient when the aircraft is rolling (all wheels on the ground).
The drag coefficient when the aircraft is rolling(all wheels on the ground).
The thrust (lbf) decreases with increasing velocity (ft/s) as shown here again.
This method (Method 3) takes into account the decrease in thrust with increasing velocity.
This is the distance that the aircraft consumes while the wheels are in contact with the ground.
An assumption is made here that states that the time to rotate is 2/10 seconds.
This is the ground roll distance of the aircraft.
Takeoff Runway Limit
Takeoff Velocity for 55 lbf +/- 10
Take Off Distance:
Taken from Anderson's "Introduction to Flight" page 332-333.
This is the maximum turning radius for the aircraft.
This is the maximum allowable force while turning at the given maximum radius.
The maximum turning rate.
wing below stall and spar can handle moment
spar breaks
wing stalls
Thrust at Sea Level and 1000 ft
Thrust at Sea Level and 1000 ft
Drag with Groundroll Losses
Drag at Design Weight +/- 10 lbs.
Drag without Groundroll Losses