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Expert help when you need it- Q1:1. (30 points). Consider an aircraft climbing steadily in the Earth's atmo- sphere with a constant speed of 1100 km/hr. As the aircraft goes to higher altitudes, the temperature of the air changes approximately linearly with elevation at a rate of -6.6 °C/km. Assume that the temperature at sea level is 25 °C. (a) Compute the Mach number of the aircraft when it reaches an altitude of 3000 m. (b) Compute the Mach number of the aircraft when it reaches an altitude of 15000 m. (c) How does the Mach number of the aircraft vary with elevation? At what altitude does the flow around it become sonic?See Answer
- Q2:2. (30 points). A fighter jet is traveling with a velocity u = (398 m/s) i + (4.00 m/s) Ĵ+ (51.0 m/s) k relative to the earth. It fires a missile that moves at a velocity of v = (107 m/s) Î + (-10.0 m/s) ĵ + (2.00 m/s) k relative to the fighter jet. If the altitude of the fighter jet is 9000 m: (a) Find the Mach number of the missile an instance after it is fired. (b) Do we have to worry about compressibility effects when analyzing the missile's flight?See Answer
- Q3:3. (30 points). You go on vacation and return to find a wind tunnel in your lab is filled with a mystery gas that is either nitrogen (k = 1.400) or helium (k = 1.667). Your colleague has left you a post-it note saying that she determined the temperature to be 293 K, the Mach number to be 1.2, and the wind speed to be 1208 m/s. (a) Which gas fills the wind tunnel? (b) What would the wind speed be if the wind tunnel was filled with the other gas?See Answer
- Q4:4. (30 points). A liquid is initially at 30 °C and 1 atm. It is heated to a temperature of 70 °C at a constant pressure. The change in density is -1.804 percent. (a) What is the liquid? (b) What is the change in density if this liquid is compressed to 75 atm at a constant temperature of 30 °C? (c) Is this liquid significantly compressible?See Answer
- Q5:Determine: a) πHPс and πLPC b) ec c) Step (time) d) Pt3, Tt3, e) Explain how you determine the change of mass flow rate of the Bleed as function of its Area f) Show all calculations to determine the Pt3 and Tt3 and any other item. g) Explain what is the bleed purpose in this case (show reference in APA v6 or v7 form) h) Show why Mbleed = 1See Answer
- Q6:Find and print in table a) Time change by step, bleed Area, m bleed and mass flow rate to combustor for each time step b) Static Temperature at stage 3 for each time step c) Mach number exit of the HPC for each time step Special Homework for 50 points d) Velocity exit of the HPC for each time step e) Plot M3 vs time, and V3 (ft/s) vs time (s) in the same chart with yy axisSee Answer
- Q7:Show calculations 1. How to determine that Mbleed is 1. 2. Par Tur Tor Por T₁2, P₁2 3. meore 4. Mach number when bleed is fully closed Mach number when bleed is fully open 5. 6. How you determine the change of the bleed area? Note: number of items is given by the user (n). It can be changed and the program provide the manner to accept any n. y-i Tc = πy where ec is the polytropic efficiency and is around of 88% 92%See Answer
- Q8: A jet engined aircraft is required to cruise for 3000 km at a constant altitude of 8 km. At the end of cruise the aircraft will weigh 112.4 kN.The wing area of the aircraft is 80 m², CD for the flight is 0.04, CL is 0.3 and the aircraft's thrust specific fuel consumption is 10-5 kg N-1 s-¹. How much fuel will be used in the cruise? The answer should have units of kN.See Answer
- Q9: The jet engines of an aircraft produce amaximum thrust, Tmax that is proportional to density:9 Tmax= The wing surface area of the aircraft is 71 m².What zero lift coefficient of drag, CDO will the aircraft have if its absolute ceiling is atan altitude of 10 km and its maximum cruisespeed is 199 m s¹ at an altitude of 8 km?See Answer
- Q10: A propeller-driven aircraft has a maximum endurance of 14.1 hours when flying according to cruise climb conditions. What is the range of the flight if the aircraft's speed is 68 m s™¹, the propeller efficiency is 0.85 and the specific fuel consumption is 10-7 kg W-¹ s-¹? The answer should have units of km.See Answer
- Q11: 2. Briefly explain the following concepts (a) Wetted aspect ratio (b) Rubber-engine sizing (c) Mission profile (d) Thrust matchingSee Answer
- Q12: 3. Explain on the effects of the following aerodynamic/wing characteristics. You can simply summarize what is written in the textbook. (a) Airfoil thickness ratio (b) Aspect ratio (c) Wing sweep (d) Wetted aspect ratioSee Answer
- Q13: 1. Consider the ASW design example in Chapter 3. (a) What would be the estimate of takeoff gross weight (using the method in Chapter 3) if the requirement of the cruise speed changes to: Mach 0.25, and Mach 0.85. Consider a turboprop engine for the first case. (b) What would be the estimate of takeoff gross weight (using the method in Chapter 3) if the requirement of the (one-way) cruise range speed changes to: 1000 miles and 2000miles. (c) What would be the estimate of takeoff gross weight (using the method in Chapter 3) if the requirement of the loitering period at the mission location changes to : 2 hrs and5 hrs. (d) The aspect ratio used in the textbook example was 7. What would be the takeoff gross weight, if this value changes to 5.5?See Answer
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