Solving 1st question
Lift=pressure*area=10935 N
(b) cargo=10935-(1111*9.8)=47.2N
5. (a) (5 pts) The lift of an airplane wing is the difference in pressure above...
An airplane wing generates lift due to a difference in air speed above and below the wing. If the wings are both at the same height, what term is the same on both sides of the Bernoulli equation? Calculate the change in pressure (P-bottom - P_top) a wing experiences if the air moves at 245 m/s above the wing and 222m/s below the wing. The density of air is 1.29kg/m^3. Calculate the lift force the plane experiences if it has...
QUESTION 13 An airplane is kept aloft by way of lift (pressure differential) on the wings. Given that a particular plane has a total wing surface area of 100 m 2 and has a mass of 20,000 kg, what is the magnitude of the difference in pressure between the bottom and top of the wings? O A 1960 N/m OB. 3070 N/m OC. 3920 N/m OD 4560 N/m O E 7840 N/m
An airplane has an effective wing surface area of 21.9 m2 that is generating the lift force. In level flight the air speed over the top of the wings is 70.0 m/s, while the air speed beneath the wings is 47.0 m/s. What is the weight of the plane?
Use the worked example above to help you solve this problem. An airplane has wings, each with area 3.95 m2, designed so that air flows over the top of the wing at 249 m/s and underneath the wing at 225 m/s. Find the mass of the airplane such that the lift on the plane will support its weight, assuming the force from the pressure difference across the wings is directed straight upwards.
Use the worked example above to help you solve this problem. An airplane has wings, each with area 3.95 m2, designed so that air flows over the top of the wing at 249 m/s and underneath the wing at 225 m/s. Find the mass of the airplane such that the lift on the plane will support its weight, assuming the force from the pressure difference across the wings is directed straight upwards.
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7m a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7mm a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
PRACTICE IT Use the worked example above to help you solve this problem. An airplane has wings, each with area 4.05 m2, designed so that air flows over the top of the wing at 249 m/s and underneath the wing at 226 m/s. Find the mass of the airplane such that the lift on the plane will support its weight, assuming the force from the pressure difference across the wings is directed straight upwards. Your response differs from the correct...
EXAMPLE 7-8 Lift on a Wing Some aeronautical engineers are designing an airplane and wish to predict the lift produced by their new wing design (Fig. 7-31). The chord length L of the wing is 1.12 m, and its planform area A (area viewed from the top when the wing is at zero angle of attack) is 10.7 m2. The prototype is to fly at V = 52.0 m/s close to the ground where T = 25°C. They build a...
(7 points) 2. For the planform below: Cr If cr 1 ft, c.-0.5 ft, b 100 psf) compute: 5 ft and Л1.E-30°, Lift coefficient (CL-1.0) and dynamic pressure (q a. The taper ratio b. The wing area c. The aspect ratio d. The mean geometric chord e. Lateral location of the mean geometric choro f. The longitudinal location of the mean geometric chord g. The lift force 1 point 1 point 1 point 1 point 1 point 1 point 1...