Class Exercise: As shown in the Figure, air deflectors are used to reduce the drag on a truck. A reduction in drag coefficient from 0.78 to 0.58 was achieved when the deflectors are installed. Calculate the power saving by the installation of the deflectors at speed of 100 km/h and the projected area is 8.36 m2. p=1.2kg/m C 0.78 C0.58 24 Chapier 11

Class Exercise: As shown in the Figure, air deflectors are used to reduce the drag on a truck. A reduction in drag coefficient from 0.78 to 0.58 was achieved when the deflectors are installed. Calculate the power saving by the installation of the deflectors at speed of 100 km/h and the projected area is 8.36 m2. p=1.2kg/m C 0.78 C0.58 24 Chapier 11

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

q: An aircraft is flying straight and level at a certain altitude with a velocity of 214 fps. Determine the power required if the wing area is 115 ft? and the total drag coefficient is 0.067. Assume SSLC (p=0.002377 slug/ft3). Provide answer in ft-Ib/s. and round off to the nearest whole number. Solve using standard English units.
Calculate the Road load power for the case Toyota Prius (fronatal area =0.8m2 sliding over a street has coefficient of rolling resistance CR= 0.015, drag coefficient CD=0.26 air density=1.2 kg/m3 the mass of the car 1500 kg. O a. 3.48 kW O b. 2.15 kW O . 9.72 kW
Aircraft flying at an altitude of (3 Km) with a velocity of (100 m/sec). The planform area of the wing is (206 m² ). Find the overall drag force acting on this aircraft if you have the following data :- Aspect ratio= 10, Weight of the aircraft = 7.5 x 105 kg.m/s² Span efficiency factor = 0.95 Wing cross section is NACA 4412 airfoll Drag coefficient = 0.006
Q1: Find the boundary layer thickness (8) equation, the shear stress (to) and the coefficient of drag (C₁) if the velocity distribution in the laminar boundary layer over the face of a spillway was observed to be: (40%) 2 5 --0-0-0) = 2 + Then calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 0.25m long and 0.5m wide at a velocity 1 m/s, take the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are C₁ and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; = Lincomp C₁₁ (α-αL=0); C₁: La Co=cat C₁² Te AR CLincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 CDi C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5
Q1: Find the boundary layer thickness (6) equation, the shear stress (to) and the coefficient of drag (C₁) if the velocity distribution in the laminar boundary layer over the face of a spillway was observed to be: u 7- (C)-()*+C)*. U Then calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 0.25m long and 0.5m wide at a velocity 1 m/s, take the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
3) An advertising sign mounted on the roof of a car is 33 inches tall, 15 inches wide and 54 inches long (airflow direction). The underside of the sign is flush with the top surface of the roof. Take air properties to be: p = 0.075 lbm/ft' and u= 1.22x10 lbm/ft.sec. Used a pressure drag coefficient of 1.2 for the advertisement sign. Calculate the total drag on the sign and the power required to overcome its effect if the car is travelling at a constant speed of a) 12 mph and b) 45 mph. Note: Provide a schematic diagram (sketch) of the problem configuration (if applicable). Every numerical calculation must be preceded by the appropriate equation. Do not forget units & dimensions during your calculations.
Q1: Find the boundary layer thickness (6) equation, the shear stress (to) and the coefficient of drag (Cò ) if the velocity distribution in the laminar boundary layer over the face of a spillway was observed to be: *--(C)- ()*+C). U Then calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 0.25m long and 0.5m wide at a velocity 1 m/s, take the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
Problem 06.002 - Calculate total drag An airplane weighing 5,000 lb is flying at standard sea level with a velocity of 525 mi/h. At this velocity, the L/D ratio is a maximum. The wing area and aspect ratio are 200 ft² and 8.5, respectively. The Oswald efficiency factor is 0.93. Calculate the total drag on the airplane. Assume poo = 0.002377 slug/ft³. The total drag on the airplane is lb.
A group of researchers from UMP conducted a project collaboration with an aircraft company to develop a small aircraft. The aircraft is designed to carry up to 2800 kg of total mass. The wing area of the aircraft is 30 m2. During takeoff, the lift coefficient of the aircraft is 0.45. Meanwhile during cruising, the drag coefficient of the aircraft is 0.035. ii. Determine the load of the wing
For the vehicle whose specifications are given below, calculate the engine power required in kW to climb up a slope of 12% (40 + XY) with a constant speed of km / h and upwind at a speed of 12 km / h. Mass: 1396 kg Load Breakdown (f / r): 61/39% Length width Height: 4556/1745/1372 mm Drag Coefficient: 0.31 Max. Motor Power: 5750 rpm for 84 kW Max. Torque: 3750 rpm for 157 Nm Max. Motor speed: 6500 rpm Gear Ratios: 3.42, 2.14, 1.45, 1.03, 0.77 Differential Ratio: 3.84 Tires: 185/65 VR 14 SBR Tire Pressure (f / r): 2.0 / 1.9 kgf / cm2
A group of researchers from UMP conducted a project collaboration with an aircraft company to develop a small aircraft. The aircraft is designed to carry up to 2800 kg of total mass. The wing area of the aircraft is 30 m2. During takeoff, the lift coefficient of the aircraft is 0.45. Meanwhile during cruising, the drag coefficient of the aircraft is 0.035. iii. Evaluate the required power to maintain at cruising speed of 300 km/h.