Solution 1 Exercise 5 Selected Aircraft from module 3 amp 4 NACA 4412 2 Aircraft Maximum Gross Weight lbs from module 3 amp 4 15 000 lbs
Solution Exercise Selected Aircraft from module amp NACA Aircraft Maximum Gross Weight lbs
Solution Exercise Selected Aircraft from module amp NACA Aircraft Maximum
Aircraft from module amp NACA Aircraft Maximum Gross Weight lbs from module amp lbs
Solution Exercise Selected Aircraft from module amp NACA
Aircraft Maximum Gross Weight lbs from module amp lbs
Solution Exercise Selected Aircraft from module
Solution Exercise Selected
(Solution) 1 Exercise 5: Selected Aircraft (from module 3 & 4): NACA 4412 2. Aircraft Maximum Gross Weight [lbs] (from module 3 & 4): 15,000 lbs....

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The weight used in the document is 15000 lbs., it needs to be redone with an aircraft weight of 8800 lbs.1 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): NACA 4412 2. Aircraft Maximum Gross Weight [lbs] (from module 3 & 4): 15,000 lbs. 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.) This document was developed for online learning in ASCI 309. File name: Ex_5_Aircra± Performance Updated: 07/19/2015

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