5. The mission profile for a 4-engine jet aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to an altitude of 20000 ft followed by a cruise distance of R₁ nm at 350 kts, climb to an altitude of 35000 ft, followed by a cruise distance of R2 nm at 450 kts descent to 10000ft followed by one hour loiter and flight to an alternate airport at R3 nm distance both at 250 kts, descent to landing approach condition followed by the final landing, taxi and shutdown. The total distance during the cruise segments and flight to an alternate airport is restricted to a maximum of 5100 nm. Based on the existing manufacturers' data you may use the information provided in Table QA-1. L/D cruise at 20000 ft altitude L/D cruise at 35000 ft altitude 18 20 L/D at 10000 ft altitude (loiter and flight to an alternate airport) C;: Specific Fuel Consumption at cruise segments C;: Specific Fuel Consumption during loiter and flight to an alternate airport Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown Table QA1-1 16 0.43 lbs/hr/lbs 0.50 lbs/hr/lbs 0.992 0.996 0.996 0.992 0.996 0.992 No provisions are made for the reserved fuel or any trapped oil and fuel. The aircraft carries 200 people (including pilots and the cabin crew) at 175 lbs each and 90 lbs baggage each. You are given that during the cruise segment at 20000 ft the aircraft weight has been reduced by 18903.6 lbs. The wing of the aircraft has an area of 3000 ft² with an aspect ratio of 10.0. Additionally, the drag equation for the aircraft at its clean condition is given as: CD = 0.0228 + C² пае a- Sketch the mission profile with clear annotations and numbering. b- Determine the gross take-off weight of the aircraft +⠀⠀ Calculation of Flight to Another Airport W W9 In( W10 altitude × cj XV 100 × 0.5 = 16 x 250 W5 Calculation of Cruise WA W9 100 x 0.5 In( W10 16 x 250 W9 In( -): = 0.03125 W10 W9 eln(W) = 0.03125 W9 = 1.031743407 W10 W10 1 W9 1.031743407 W10 = 0.9692332349 W9

As speed as possible please

Derive the expression for the ground length during take-off in aircrafts.

3) The ME Department just purchased a new mega-drone that weighs 220 lbs and can descend autonomously to land on its own. The drone company included the graph shown below for how much force is applied to the Thrust 'T'. If the operator allows the autonomous descent when the drone has an initial downward velocity of 2 ft/s, calculate the velocity of the drone after 3 seconds. T, Ibf V = 2ft/s 260 t, (s) 5:57 PM O 57°F Mostly sunny 3/6/2022 99+ P Type here to search Del PrtScn FB Home F9 End F10 PgUp PgDn F12 F11 F6 F7 F5 F4 Esc F2 F3 F1 Backspace & @ %23 2$ % 8 4. Y U Q W

Part A: What is the period of the spacecraft's orbit?     T=___s Part B: Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee.       (Vperigee)/(Vapogee)=___ Part C: Using conservation of energy, find the speed at perigee and the speed at apogee.       Vperigee,Vapogee=___m/s Part D: It is necessary to have the spacecraft escape from the earth completely. If the spacecraft's rockets are fired at perigee, by how much would the speed have to be increased to achieve this?      delta(perigee)=___m/s Part E: What if the rockets were fired at apogee?       delta(apogee)=___m/s Part F: Which point in the orbit is more efficient to use and why?

Q2 [Type B]: A 2 kg ball is attached to a 1 m cable and is released from rest from Point A, as shown in the diagram. Determine the speed of the ball and the tension in the cable when the ball passes the lowest point, Point B. A 1m 40⁰ Shaobo Huang B

Consider a fuel cell vehicle. The vehicle draws 30 kW of power at 60 km/hr and is 50% efficient at rated power. (It converts 50% of the energy stored in the hydrogen fuel to electric power.) You are asked to size the fuel cell system so that a driver can go at least 300 km at 60 km/hr before refueling. Specify the minimum volume and mass requirements for the fuel cell system (fuel cell + fuel tank) given the following information:a. Fuel cell power density: 1 kW/L, 500 W/kg b. Fuel tank energy density (compressed hydrogen): 4 MJ/L, 70 MJ/k

A string is wound around a pulley of diameter of 0.2 m. One of its ends is tied to the pulley and the other end to a weight hanging freely. The weight falls a distance of 4 m from the rest in 3 s. Determine the total distance through which the weight should fall so that the velocity of the pulley will be 400 rpm. OPTIONS: 1.Around 10 m 2.Around 15 m 3.Around 12 m 4.Around 6 m 5.Around 8 m 6.None

بلا زحمة شلون يحلون هذا السؤال

The terminal velocity is when dv/dt = 0 and D container is negligible however what’s the value for S If the velocity is 4 m/s?