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Post gr1 AE 210S with correct answers

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What is the relationship between thrust available and power available? Power available is thrust available multiplied by velocity. Which of the following statements correctly describes the relationship between the speed for minimum thrust required and the speed for minimum power required? Minimum thrust required occurs at a higher speed than the speed for minimum power required. Maximum velocity on power available/required vs. velocity curve occurs at the same speed as the max velocity on that same aircraft's thrust and drag vs. velocity curve. True An F-16 has just completed aerial refueling, increasing its weight by 6,000 lb. Assume altitude and aircraft configuration did not change. Compared with its speed for (L/D)max prior to refueling, how would you expect its speed for (L/D)max after refueling to differ? The speed for (L/D)max would be higher. A Global Hawk aircraft must fly a mission that has the maximum possible duration. Therefore, it must fly at its speed for (L/D)max . At the same time, its operators wish to have it fly as far as possible while maintaining its (L/D)max airspeed. What altitude would you recommend for this mission? Fly as high as possible for maximum true airspeed while flying at the airspeed for (L/D)max. A 12,000-lb T-38 is flying at M = 0.5 at 10,000 ft using military power. Based on the power available and power required chart on page 602 of your textbook what is the aircraft's specific excess power, that is, the quantity (power available minus power required) divided by the aircraft weight for these conditions? 100 ft/s Which of the following statements about jet engines is true? (there are two correct answers. Pick either one) Jet engines make thrust by pushing air out the back of the engine at a higher speed than the speed at which the air came in the front What would be the best engine choice if you were designing an aircraft that will be operating primarily at 300 KTAS and 30,000 feet? (Hint: Refer to Figure 5.4) Turboprop What is Thrust Specific Fuel Consumption (TSFC)? Fuel flow rate (lbs/hr) per pound of output thrust (lbs) If you were designing an aircraft to fly at M = 0.8, what would be the most fuel efficient engine you could choose? (Hint: refer to Figure 5.3 and lower TSFC is better...) High-bypass turbofan Afterburners are a fuel-efficient way of increasing thrust? False If you were designing an aircraft to fly at M = 0.5 and you wanted the engine with the highest thrust-to-weight ratio, which engine would you choose (Assume that a rocket is not an option)? (Hint: refer to Figure 5.2) Afterburning turbofan You are flying in your F-22 from Tyndall AFB, FL practicing intercepts. You receive a radio call stating that a dense fog bank has unexpectedly closed Tyndall and your alternate, Eglin AFB. The closest airfield with acceptable weather is Barksdale AFB, LA, some 500 NM away. Your digital mission planner indicates that you are already at the optimum cruise altitude, but that the maximum possible range you can achieve with the fuel on board is 400 NM. What should you do? Find a tanker A tanker is also on its way to Barksdale, and is about 300 NM ahead of you, but they are low on gas, too. They agree to orbit at their present position and altitude and let you catch up. What speed should you maintain on your way to the rendezvous with the tanker? Max range airspeed What speed should the tanker maintain while they orbit waiting for you to arrive? Maximum L/D airspeed. If your F-22's drag polar is given by CD = 0.0148 + 0.133 CL2, what lift coefficient should you maintain en route to the rendezvous point? Look carefully at the relationships between CD and CL at the desired performance point, max endurance or max range. Solve for the CL at that desired performance point. 0.193 Again, your F-22's drag polar is given by CD = 0.0148 + 0.133 CL2. Its wing area is 830 ft2 and it weighs 50,000 lbs at the moment. Assuming that you are flying at the tropopause on a standard day, you maintain M = 0.8 en route to the rendezvous point 300 nm away, and your TSFC at this Mach and altitude is 1.095/hr, how much gas will you burn to get there? This one will take some thought, but look at what you need. Pounds of fuel. That will come from the TSFC. Carefully review the units of TSFC and decide how you can cancel out terms to get to pounds of fuel. Consider calculating average drag and using Eq 5.39. 3,300 lb You are flying with your buddy who has challenged you on spot landings, in which you reduce power on downwind and maneuver to land without power. If you add power, you lose the bet. The one who lands closest to the approach end of the runway wins. Today you reduce power early and roll out on final lower than normal. You establish the normal (L/D)max for gear down, no flaps final approach glide speed and discover that your plane is going to land short of the runway. What should you do? Add power and go around. You lose the bet again. You are in a glide at (L/D)max, what effect will decreasing your weight (dropping payload or ejecting your back seater) have on your glide? Glide range will____________. The velocity to fly at (L/D)max will_____________ not change, decrease An 12,000 lb T-38 is in a steady climb passing 10,000 ft at 0.5 Mach on a Standard Day. What is its rate of climb using military thrust? 100 ft/s = 6,000 ft/min A 12,000 lb T-38 is in a steady climb passing 10,000 ft at 0.5 Mach on a Standard Day. What is its climb angle using military thrust? 11 degrees An F-16 has the drag polar: CD = 0.018 + .117 CL2. What is its maximum glide ratio? 11 Why must we use specific excess power rather than just excess power when comparing the acceleration capability of two different aircraft? Specific excess power is excess power divided by weight, which, when multiplied by the acceleration of gravity, gives the correct comparison of acceleration capability between two aircraft. What is Energy Height? Energy height is total mechanical energy (potential + kinetic) divided by weight, which yields

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Geüpload op: 20 januari 2025
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post gr1 ae 210s with correct answers

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Post gr1 AE 210S
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