embry ASCI309 module 1.7 Rectilinear Motion Exercise Assignment 1 latest 2016 march

Exercise
1: Rectilinear Motion
The first
part of this week’s assignment is to choose and research a turbine powered
(i.e. jet type) aircraft.You will further use your selected aircraft in
subsequent assignments, so be specific and make sure to stay relatively
conventional with your choice in order to prevent having trouble finding the
required data during your later research. Also, if you find multiple numbers
(e.g. for different aircraft series, different configurations, and/or different
operating conditions), please pick only one for your further work, but make
sure to detail your choice in your answer (i.e. comment on the condition) and
stay consistent with that choice throughout subsequent work. In
contrast to formal research for other work in your academic program at ERAU,
Wikipedia may be used as a starting point for this assignment. However, DO NOT
USE PROPRIETARY OR CLASSIFIED INFORMATION even if you happen to have access in
your line of work.Keep in mind that any theoretical solution to a complex, unique real
world problem is based on models and generalizations, requiring certain
assumptions and simplifications, and comes with a variety of limitations as to
its applicability. Therefore, detailing conditions and selections is a
fundamental part of a scientifically sound approach and documentation of your solution
to the problems.1. Selected Aircraft:2. Maximum Takeoff Weight (MTOW) [lbs]:3. Engine Type and Rated Thrust [lbs]:4. Total Available Thrust (sum of all engines for multiengine aircraft) [lbs]:5. Maximum Rate of Climb [ft/min]: 6. Take-off distance at MTOW [ft]:Uniformly
Accelerated Rectilinear Motion and Newton’s Law of MomentumEquations:
F = ma m = W/gVF
2 =VI2+ 2 a s g
= 32.2 ft/sec2VF
=VI+ a t Takeoff distance (s) = VF
2/2aKE
= ½ mV2 PE = WhHP= T*Vkts /325 sin(γ) = (ROCkts)/(Vkts)1 kt = 1.69 ft/sec Remember
to keep track of units, convert as required, and express answers in the
requested unit. (Keep in mind that the initial velocity VIfor
takeoff is zero since we start from a standstill).A. Using your
researched data from 2. and 4. above compute the acceleration on the aircraft
during the takeoff roll. [ft/sec2]
(For this exercise, disregard friction and drag influences. Also, keepin mind that weight is not the same as
mass.)B. If your
aircraft lifted off the ground at 150kts, what would be the length of the
takeoff run? [ft](Watch for
unit conversions.)C. How much
time would it take until liftoff at 150kts once the takeoff roll is started? [s](You will
have to algebraically solve the given formula for time ‘t’ first.)D. Determine how fast the airplane should be
going when it passes the 1000-foot runway marker (1000 feet from the start of
the takeoff roll)? [kts].(Apply the
distance formula as you would for the takeoff run in Question B; however, the
distance ‘s’ is now known to be 1000ft and the unknown is the velocity ‘V’.
Solve algebraically for ‘V’. Don’t forget that results will have to be
converted into kts.)Similar to
detailing assumptions and conditions at the onset, any quantitative result of
our theoretical work also requires a qualitative discussion of applicability.
The important question to discuss is how accurate 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 A through D. Compare your calculated takeoff
distance in B with your research in Question 6. What elements did we neglect in
the acceleration computed in Question A? How did it affect our further work in
B through D? (see &
compare also formula given above with the calculation examples within the
module)E. What is
the power [HP] of the aircraft
engines after takeoff at the total available thrust (from Question 4) if flying
at 200kts? (Remember, this formula already has unit conversions included)F. What is the Kinetic Energy [ft-lb] of the aircraft at 200kts and
Maximum Takeoff Weight (from Question 2)? (Remember, weight is not the same as
mass, and watch for unit conversions.) G. What is the Potential Energy [ft-lb] of the aircraft after climbing
out to 10,000ft above sea level at Maximum Takeoff Weight (from Question 2)?H. What is
the Angle of Climb [deg] for the
airplane at 200kts at the maximum rate of climb from Question 5? (Make sure to
use vertical speed, i.e. ROC, and horizontal speed, i.e. flight speed, in the
same unit and pay attention to your calculator settings for trigonometric
functions.)
Similar to
your discussion for questions A through D, comment on your E through H results.
How realistic do you think energies in question F & G were calculated?
Which assumption in those questions most probably would have changed in a real
flight and how would it have affected results?