Electricity for Refrigeration, Heating, and Air Conditioning
9th Edition
ISBN: 9781285179988
Author: Russell E. Smith
Publisher: Cengage Learning
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Question2
The mission profile for a jet driven aircraft consists of the following segments: engine
start and warm-up, taxi, take-off, climb to the cruise altitude of 35000 ft, descend to
10000 ft, one hour loiter at this altitude at 60% of the cruise speed, flight at loiter
speed and altitude to an alternate airport (100 nm), descend to landing approach
condition followed by the final landing, taxi and shutdown.
The cruise Mach number is 0.8. 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 lb each and 90 lb baggage each. This aircraft has a wing area of 2000
ft²
a) If the landing stall speed of the aircraft is set at 100 kts corresponding to a landing
weight of 0.85 Wro, and C(Lmax) Landing = 2.50, determine take-off weight and
then calculate the range and empty weight of this aircraft (see Table Q2).
Consider landing at sea level on a standard day.
L/D at cruise
L/D at 10000ft flight…
q
Y
X
A
ΕΙ
L
B
M
If L=3508 mm, W-9189 N, E=80 GPa, Determine the deflection at the free end of the beam.
Step-1
The bend moment of the beam, M (Units: N.m), as a function of spatial coordinate X ( Units: m) can be described by
Select one:
O 1. M = 16117.506 +9189.000*X, for 0<=X<= L/2; M=0.00, for L/2< x <= L
O 2. M = 16117506.000 - 9189.000*X, for 0<= x <= L/2; M = 9189.000* X, for L/2< x <= L
O 3. M=16117.5069189.000*X, for 0<=X<= L/2; M=0.00, for L/2< x <= L
O 4. M = 16117506.000 + 9189.000*X, for 0<=X<= L/2; M = 9189.000*X, for L/2
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- Question 1 A three-blade propeller of a diameter of 2 m has an activity factor AF of 200 and its ratio of static thrust coefficient to static torque coefficient is 10. The propeller's integrated lift coefficient is 0.3.arrow_forwardA close end tube of thin-walled circular section may be subjected to torque 7 and internal pressure P, as shown in Figure Q3. The shear stress in the wall caused by the torque can be calculated as T = T/(2πR²t), where the mean radius of the cross section is R (i.e., the radius of the centreline of the wall) and the wall thickness is t. The internal radius of the tube can be calculated as (R-t/2). However, as R>>t, you can approximately assume that the internal radius of the tube is equal to Rin the subsequent calculation. The tube is made from a material with Young's modulus E, Poisson's ratio v. Orr T t P Ozz бөө Orr Z T Ozz бед Figure Q3 Centreline of the wall R (a) If the change of the diameter cannot exceed 0.1 m under elastic deformation, calculate the minimum allowable wall thickness of the cylindrical pressure vessel if P=23.6 MPa, T=0 KN.m, R = 2 m, Young's modulus E = 246 GPa, and Poisson's ratio v = 0.21.arrow_forwardQuestion2 The mission profile for a jet driven aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to the cruise altitude of 35000 ft, descend to 10000 ft, one hour loiter at this altitude at 60% of the cruise speed, flight at loiter speed and altitude to an alternate airport (100 nm), descend to landing approach condition followed by the final landing, taxi and shutdown. The cruise Mach number is 0.8. 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 lb each and 90 lb baggage each. This aircraft has a wing area of 2000 ft² L/D at cruise L/D at 10000ft flight Table Q2 20 16 0.43 lb/hr/lb 0.50 lb/hr/lb C: Specific Fuel Consumption at cruise: C: Specific Fuel Consumption at 10000 ft flight: Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown 0.992 0.996 0.996 0.996 0.992 0.992 Question 2 continues on the…arrow_forward
- [(a) If the change of the diameter cannot exceed 0.1 m under elastic deformation, calculate the minimum allowable wall thickness of the cylindrical pressure vessel. (P= 23.6 MPa, T=0 KN.m, R = 2 m, Young's modulus E = 246 GPa, and Poisson's ratio v = 0.21)] Step-4 The minimum allowable wall thickness of the cylindrical pressure vessel can be calculated as (Units: mm and rounded to three decimal places) Select one O 1.8.481 O 2.4.240 ○ 3.6.869 ○ 4. 16.961 5. 13.738 O 6.3.434arrow_forward[If L=3508 mm, W=9189 N, E=80 GPa, Determine the deflection at the free end of the beam.] Step -3 Which equation in the following choices most accurately represents the functional relationship between the value of the deflection v ( Units: mm) at half length (x =L/2) of the beam and the second moment of area about z-axis of the cross section, Izz ( Units: mm²): (Please note that " X = L/2" is the same as "X=L÷2".) Select one: O 1. v 588830960.433/Izz O 2. v=338836061.442/Izz O 3. v 119832265.632/Izz O 4. v 413214709.076/Izz O 5. v=287184222.808/Izz O 6. v=206607354.538/Izz O 7. v=66114353.452/Izz O 8. v 752050770.518/Izzarrow_forwardA bar of length L and of a circular cross-section of diameter D is clamped at the top end and loaded at the other (bottom) end by a point load P as shown in Figure Q2a. The cross-section of the bar is shown in Figure Q2b indicating that load is applied at the point A. The material used in the bar has specific weight y. Find the magnitude and location of the maximum normal stress in the bar. Figure Q2 a Figure Q2 b 45° A Step -1 The given load case can be represented by a statically equivalent system of the following loads Select one: O 1. A tensile force placed at the centroid with intensity equals to 0.354 P; a bending moment about zaxis, M₂ = (P×D× 0.708); a bending moment about yaxis, My= (Px D× 0.177); and self-weight of the vertical beam producing maximum tensile stress at the built-in end. ○ 2. A tensile force placed at the centroid with intensity equals to 0.354P; a bending moment about z axis, M₂ = (PxDx 0.354); a bending moment about yaxis, My= (Px D× 0.177); and self-weight…arrow_forward
- Question 1 A three-blade propeller of a diameter of 2 m has an activity factor AF of 200 and its ratio of static thrust coefficient to static torque coefficient is 10. The propeller's integrated lift coefficient is 0.3. a) Calculate the static power and thrust coefficients.arrow_forwardA cantilever beam of a channel section and length L is loaded by a point load W applied at half-length of the beam through the centroid of the section, as shown in Figure Q1. The material of the beam is aluminum alloy with the Young's modulus of E. 1. As illustrated in Figure Q1, the Y-axis is positioned along the symmetric plane of the cross-section, while the Z-axis and X-axis pass through the centroid of the cross-section. The X-axis is defined using the right-hand rule, with the origin located at the fixed end. The distance from the centroid to the bottom of the cross- section, yc (Units: mm), is: Select one: O 1. 48.72 O 2. 70.24 ○ 3. 76.38 ○ 4. 83.12 O 5. 68.73 ○ 6. 50.26 ○ 7. 56.19 ○ 8. 88.73 ○ 9. 62.82 O 10. 42.83 W a a 25 mm y Z AN a-a 25 mm 150 mm SC yc 6 mm Figure Q 1 200 mmarrow_forwardUse the principle of virtual work to determine the vertical deflection and rotation at tip (Point B) of the cantilever shown below. (L=6847 mm, q=5331 N/mm, M = 1408549 N.mm, and El = 8.6 x 1014 N. mm²) 9 Y M A ΕΙ B Larrow_forward
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