Solution Exercise Selected Aircraft from module amp Aircraft Maximum Gross Weight lbs

Solution Exercise Selected Aircraft from module amp Aircraft Maximum

Aircraft from module amp Aircraft Maximum Gross Weight lbs from module amp

Solution Exercise Selected Aircraft from module amp

Aircraft Maximum Gross Weight lbs from module amp

Solution Exercise Selected Aircraft from module

Solution Exercise Selected

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Paper instructions

Can you please complete ex 5? Attached are 3 and 4 that you've already completed and you'll need the information from the previous assignments. 1
This document was developed for online learning in ASCI 309.
File name: Ex_5_Aircraft Performance
Updated: 07/19/2015
Exercise 5: Aircraft Performance
For this week’s assignment you will revisit your data from previous exercises, therefore
please make sure to review your results from the last modules and any feedback that you
may have received on your work, in order to prevent continuing with faulty data.
1. Selected Aircraft (from module 3 & 4): 2. Aircraft Maximum Gross Weight [lbs] (from module 3 & 4): Jet Performance In this first part we will utilize the drag table that you prepared in module 4. Notice that the total drag column, if plotted against the associated speeds, will give you a drag curve in quite similar way to the example curves (e.g. Fig 5.15) in the textbook. (Please go ahead and draw/sketch your curve in a coordinate system or use the Excel diagram functions to depict your curve, if so desired for your own visualization and/or understanding of your further work.) Notice also that this total drag curve directly depicts the thrust required when it comes to performance considerations ; i.e. as discussed on pp. 81 through 83, in equilibrium flight,
thrust has to equal drag, and therefore, the thrust required at any given speed is equal to the
total drag of the airplane at that speed.
Last but not least, notice also that, so far, in our analysis and derivation of the drag table in
module 4, we haven’t at all considered what type of powerplant will be driving our aircraft. For all
practical purposes, we could use any propulsion system we wanted and still would come up with
the same fundamental drag curve, because it is only based on the design and shape of the
aircraft wings.
Therefore, let’s assume that we were to power our previously modeled aircraft with a jet
engine.
A. What thrust
[lbs]
would this engine have to develop in order to reach 260kts in level flight at
sea level standard conditions? Notice again that in equilibrium flight (i.e. straight and level, un-
accelerated) thrust has to be equal to total drag, so look for the total drag at 260kts in your
module 4 table. (In essence, this example is a reverse of the maximum speed question –
expressing it graphically within the diagram: We know the speed on the X-axis and have the
thrust required curve; that gives us the intercept point on the curve through which the
horizontal/constant thrust available line must go.)
B. Given the available engine thrust from A. above, what is the Climb Angle
[deg]
at 200kts and
Maximum Gross Weight? (Notice that climb angle directly depends on the available excess
thrust, i.e. the difference between the available thrust in A. above and the required thrust from
your drag curve/table at 200kts. Then, use textbook Eq. 6.5b relationships to calculate climb
angle).

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