Gas Dynamic Lab: 04: Select the correct answer for the following questions. 1. Lift is the component of this force that is . to the oncoming flow direction. (a) parallel, (b) with angle, (c) perpendicular 2. Does lift and drag of an airfoil depend on angle of attack? (a) True (b) False 3. Is airfoil shape similar to blades of the propeller? (a) True (b) False 4. Is airfoil can be characterized by the relation between the angle of attack, lift coefficient and drag coefficient? (a) True (b) False 5. The symbol means in the figure. (a) lift force (b) drag force (c) normal force Angle of attack

Gas Dynamic Lab: 04: Select the correct answer for the following questions. 1. Lift is the component of this force that is . to the oncoming flow direction. (a) parallel, (b) with angle, (c) perpendicular 2. Does lift and drag of an airfoil depend on angle of attack? (a) True (b) False 3. Is airfoil shape similar to blades of the propeller? (a) True (b) False 4. Is airfoil can be characterized by the relation between the angle of attack, lift coefficient and drag coefficient? (a) True (b) False 5. The symbol means in the figure. (a) lift force (b) drag force (c) normal force Angle of attack

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

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(b) A wind-tunnel experiment is performed on a small 1:5 linear-scale model of a car, in order to assess the drag force F on a new full-size car design. A dimensionless "drag coefficient" Ca is defined by C, =- pu'A where A is the maximum cross-sectional area of the car in the flow. With the model car, a force of 3 N was recorded at a flow velocity u of 6 m s. Assuming that flow conditions are comparable (i.e., at the same Reynolds number), calculate the expected drag force for the full-sized car when the flow velocity past it is 31 m s (equivalent to 70 miles per hour). [The density of air p= 1.2 kg m.]
A: An aircraft flying steady and level at true airspeed of 720 km/hr at sea level. The aircraft have two engine at 85.4kN thrust each and drag polar equation is CD-0.035+0.05 CL2, wing area is S-187m². What is aircraft weight? Cal. na?
Q.10. To predict the drag on an aircraft at a flight speed of 150 m/s, where the condition of air is such that the local speed of sound is 310 m/s, a pressurized low temperature tunnel is used. Density, viscosity and local sonic velocity at tunnel condition are 7.5 kg/m³, 1.22 x 10-5 Ns/m² and 290 m/s. Determine the flow velocity and the scale of the model. Assume full dynamic similarity should be maintained. Density and viscosity at the operating conditions are 1.2 kg/m³ and 1.8 x 10 Ns/m².
The maximum lift-to-drag ratio of a 600,000 lb aircraft is 18.7. The Thrust Specific Fuel Consumption (TSFC) = 0.85 (lbs/hr)/lb. The total fuel on board is Wf = 180,000 lbs. Find the maximum endurance of the aircraft in hours. Round off your answer in ones place. Answer for a thumbs up
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.
FLUID DYNAMICS (AERO) Complete solution, units and fbd if possible Required to find: 1. ) CL ( Coefficient of lift ) and 2.) Thickness Ratio of airfoil UP VOTE<<
(c) In a wind tunnel experiment, a drag force on 1:8 scale model billboard is 1 kN. The air in the wind tunnel is 20 degree Celsius. During a storm, the wind speed can reach 20 km/hr with air temperature of 10 degree Celsius. Determine the drag force experience by the billboard during storm. Refer Appendix B.
8.) A circular cylinder 4m long and 3m in diameter is in an air stream. The flow velocity is 5 m/s L parallel to the axis of the cylinder. Given that the coefficient of drag, CD on the cylinder is 1.3, and the density of air is 1.225 kg/m3. What is the force on the cylinder? A. 0.090 KN B. 0.14 KN C. 0.24 KN D. 0.91 kN
b) Air at temperature of 60 °C moves over a long flat plate with a uniform free stream velocity of U= 900 m/s. Assume the boundary layer formed above the surface of the plate starts at the tip of the leading edge and the velocity profile inside the boundary layer has power-law form as 0.15 U where u is the velocity inside the boundary layer, y is the vertical axis and 8 is the boundary layer thickness. Determine the: i) boundary layer displacement thickness, 8 as a function of 8 , ii) boundary layer momentum thickness, 0 as a function of 8, iii) boundary layer thickness, & as a function of Reynolds number and x using Von Karman Integral Method, and iv) boundary layer thickness, & at a position x = 350 cm away from the leading edge of the plate.
3. Suppose the drag force on a truck is given by the equation: F = cqu² + c2v where c = 4.80 N and c, = 111.8 N. Check that this relationship is plausible. Do the units work out? (a) Calculate the required propulsive power at a speed of 55 mi/hr. Express your final answer in Hp. Recall that 1Hp= 745.7 W. (b) Calculate the required propulsive power at a speed of 80 mi/hr. (c) Is the ratio of required powers proportional to the ratio of given speeds? Surprised? Or not?
a test tank will be used to measure the drag of a scale model ship 0.8 m long. This model bears full resemblance to a 40 m long prototype ship that was designed to sail at a speed of 10 m / s. Evaluate: a) the speed of the model take the number of froud into account in your analysis.
The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s It may be assumed that 1knot = 0.51444 m/s