Textron Airland Scorpion Then provide the following:

1. Maximum Takeoff Weight (MTOW) [lbs]:

1. Engine and Rated Thrust [lbs]:

1. Total Available Thrust (sum of all engines for multiengine aircraft) [lbs]:

1. Maximum Rate of Climb [ft/min]:

1. Take-off distance at MTOW [ft]:

Uniformly Accelerated Rectilinear Motion and Newton's Law of Momentum

Equations:

F = ma m = W/g

A=F/M g = 32.2 ft/sec²

Takeoff distance (s) = V_F²/2a

KE = mV² PE = Wh

HP= T*V_kts /325

1 kt = 1.69 ft/sec

* Remember to keep track of units, convert as required, and express answers in the requested unit.

Next complete the following:

1. Find the mass of your aircraft. (m = W/g)

1. Find the Acceleration of your aircraft using the total thrust you found. (A=F/Mass. Note in this case F=Force of Total Thrust of your engines)

1. If your aircraft lifted off the ground at 150kts, what would be the length of the takeoff run (in feet)? (Takeoff distance (s) = V_F²/2a. Watch for unit conversions.)

1. The time t [S] it took for this Takeoff.

Similar to detailing assumptions and conditions at the onset, any quantitative result of our theoretical work also requires a qualitative discussion of applicability. The critical question to discuss is how accurately our result will depict the real world. Possible errors should be identified, our certainty about results evaluated, and additional recommendations for further improvement provided.

Therefore, comment on your findings in Questions #1 through #3. Compare your calculated takeoff distance in #3 with your research above in item E. What elements did we neglect in the acceleration computed in Question #1? How did it affect our further work in #2 and #3?

1. What is the power [HP] of the aircraft engines after takeoff at the total available thrust from item B (found above) if flying at 200kts? (HP= T*V_kts /325 - (T is Total Thrust).Remember, this formula already has unit conversions included.)

1. What is the Kinetic Energy [ft-lb] of the aircraft at 200kts and Maximum Takeoff Weight (KE = mV² -from item B above)?

1. What is the Potential Energy [ft-lb] of the aircraft after climbing out to 10,000ft above sea level at Maximum Takeoff Weight (PE = Wh W is WT and H Is Height from item B)?

1. What is the Total Energy of the aircraft using questions 5 & 6 above? (TE=KE +PE)