ler angles of attack, which is associated wi Diffuser effect Дифузорно течение O a decrease in Lift and an increase in Drag a decrease in Lift and an increadecrease se in Drag
Q: . 5.20 Suppose you are designing a parachute with a drag coefficient of 0.5. What cross-sectional…
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Q: Explain how the three wing planforms, shown below, could while having different have the same local…
A: Given Wing Planforms To find Local lift distribution is elliptical different local lift coefficient
Q: A shuttlecock is launched from the ground with an initial speed of 37.3135 m/s at an angle of 7.8471…
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Q: For a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd…
A: Given DataM=2Cd=0.082Cd=0.093α=4°
Q: Qustion. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2…
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Q: A shuttlecock is launched from the ground with an initial speed of 34.6092 m/s at an angle of 5.462…
A: Given When drag force becomes equal to weight net force is zero Final velocity can be determined as
Q: By which part of the Aircraft is mainly produced the "Induced drag" ??
A: Lift causes induced drag, which is unavoidable.
Q: Figure 2 shows a 0.25 kg kite with an area of 0.65 m² flies in a 25 km/h wind such that the…
A: Vector is a physical quantity that has magnitude and direction both. Scalar is a physical quantity…
Q: When testing a new car, the car drives with a constant speed v = 140 km/h. The power of car’s engine…
A: Given data: The constant speed is of the car is v = 140 km/h. The power of car's engine is P = 120…
Q: What is the effective angle of attack ? What is the induced drag ? Show them by drawing a sketch and…
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Q: The power delivered to the wheels of a car is used to overcome aerodynamic drag. Compare the amount…
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Q: wing and induced drag coefficient!
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Q: A skydiver jumps from (5.5000x10^3) m with no parachute into a giant net. The mass of the skydiver…
A: Given data Mass of skydiver = m = 1.05 x102 kg = 105 kg Projected Area = A = 0.45 m2 Pressure = P =…
Q: A small aircraft has a wing area of 37 m2, a lift coefficient of 0.45 at takeoff settings, and a…
A: Given data Wing area = 37 m2 Lift coefficient = 0.45 Total mass = 4300 kg Speed = 300 km/h =83.33…
Q: A skydiver jumps from (5.000x10^3) m with no parachute into a giant net. The mass of the skydiver is…
A: Given data: Mass of skydiver = m = 1.05 x 102 kg = 105 kg Projected Area = A = 0.45 m2 Pressure = P…
Q: Explain briefly what is meant by drag and its form.
A: Drag is the force that opposes the motion of the aircraft through the air. It is generated by the…
Q: Kindly give me both right solutions with clear calculations The drag polar of a glider is given by…
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Q: The air flows past a 1m diameter disk oriented normal to upstream flow at 6.8m/s. The pressure…
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Q: Fairings are attached to the front and back of a cylindrical body to make it look more streamlined.…
A: Drag forces arise from pressure differences over the body (due to its shape) and frictional forces…
Q: What is the effect of Reynolds number on drag coefficient , lift coefficient and L/D ratio
A: The lift-to-drag proportion increases as the Reynolds number increases for both the airfoils…
Q: The sphere of diameter of 5.0 cm is moving in still water at a velocity of 2.0 m/s. The drag…
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Q: 2-Air at 30 C over a flat plate at speed of 1.2 m/sec. Calculate the boundary layer thickness at…
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Q: Explain how Foilsim determines lift and drag.
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Q: Consider experimental images of air flow over symmetrical airfoils shown in Figure 1. Discuss and…
A: We will answer the first question since the exact one wasn't specified. Please submit a new question…
Q: n air at 25°C and latm. Use drag coefficient Cp = 0.4 and Whitak e spheres fall at their terminal…
A: we know thatRe=ρuDμ=uDνwhere,Re=Reynolds number ρ= density D= diameter…
Q: Discuss the importance of lift and drag with the help of examples.
A: we will discuss the importance of drag & lift by an example of aeroplane aerofoilsection
Q: A 0.80-m-diameter, 1.2-m-high garbage can is found in the morning tipped over due to high winds…
A: Draw diagram of can when it is just to lift about point P, Given
Q: An airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift…
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Q: What effect does increasing the Reynolds number have on coefficient of lift and drag?
A: we know that Reynolds no. is defined as the ratio between flow inertia and viscosity.
Q: 5) A wedge airfoil is placed in a supersonic flow at M 2. G. Calculate the lift and drag…
A: Given: The Mach number, M = 2.G = 2.2 The angle of attack, α = 4°
Q: (a) A luxury sports car has a frontal area of 23.1 ft and a 0.24 coefficient of drag at 80 mph. How…
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Q: In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required…
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Q: cool not coPP I in air at 25°C and latm. Use drag coefficient C the spheres fall at their terminal…
A: Re =ρVDμ =VDν chracterstics of air at Ts+T∞2=300+3502= 325 K using data book ν =5.12×10-5m2/s k =…
Q: In a well designed wing, which of the following would best describe the lift to drag ratio? O a.…
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Q: Bill gets a job delivering pizzas. The pizza company makes him mount a sign on the roof of his car.…
A: The Work drag is W=12ρairAV2CDL where CD = 0.94 Average speed, V =45 mph…
Q: a) A group of researchers from UMP conducted a project collaboration with an aircraft company to…
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Q: Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5°
A: Given: Mach number =2.6 angle of attack=5 To determine: Lift and rag coefficient
Q: - Use FoilSim to investigate how an aircraft wing produces lift and drag by changing the values of…
A: An airfoil produces lift by applying a downward constrain on the air because it flows past.…
Q: A jet plane weighing 29.4 kN and having a wing area of 20 m flies at a velocity of 950 km/h. When…
A: Given: Weight of the plane=29.4kN Area of the wing = 20m2 Velocity of the plane=950km/hr or…
Q: The manufacturer of a car reduces the drag coefficient of the car from 0.38 to 0.33 as a result of…
A: Given data: The initial drag coefficient, cd1 = 0.38. The final drag coefficient, cd2 = 0.33. The…
Q: How does the Reynolds number effect the lift and drag coefficient for a symmetrical airfoil
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Q: - Study how the lift and drag varies with a change in angle of attack for a flat plate, symmetrical…
A: The impact is called induced drag or drag due to lift. The flow around the wingtips of a finite…
Q: Calculate lift, drag and (T/W) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag…
A: Given, V = 500 m/s A = 45 m2 CD = 0.05 CL = 0.9
Q: The rectangular wing of a smal airplane has a chord length of 1.8 m and a wingspan of 10 m. When its…
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Q: Explain the causes of Lift and Drag on the illustration below:
A: The component of the aerodynamic force that is perpendicular to the flow direction is known as…
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- Engine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the thickness of the hydrodynamic boundary layer at a distance 0.3 m from the leading edge of the surface.A shuttlecock is launched from the ground with an initial speed of 36.9838 m/s at an angle of 9.9728 degrees with respect to the horizontal. The shuttlecock experiences air resistance with a drag coefficient of 0.1967 in an environment where the air density is 0.7584 kg/m3. If the shuttlecock has a radius of 3.4 cm and a mass of 5.2 grams, what is the maximum height reached by the shuttlecock? Assume that the experiment is done near the surface of the earth.An airplane is cruising at a velocity of 950 km/h in air whose density is 0.526 kg/m3. The airplane has a wing planform area of 90 m2. The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is (a) 21,500 kW (b) 19,300 kW (c) 23,600 kW (d ) 25,200 kW (e) 26,100 kW
- A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is 0.312 kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012 , determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome wing drag.Explain boundary layer thickness?A commercial airplane has a total mass of 150,000 lbm and a wing planform area of 1700 ft2. The plane has a cruising speed of 625 mi/h and a cruising altitude of 38,000 ft where the air density is 0.0208 lbm/ft3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and drag characteristics of the wings can be approximated by NACA 23012, determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome drag. Take the air density on the ground to be 0.075 lbm/ft3.
- Calculate the frontal area of a parachute of hemi-spherical shape which will allow aparachutejumper of weight 90 kg to descend with a steady velocity of 8 m/s ignoring air movement.The drag coefficient of parachute as determined from experiments is 1.5. Take the densityof air as 1.2 kg/m37. A flat plate has a length of 40 cm and width of 1 m. Air, at pressure of 2 atm,temperature of 57 C, and velocity of 3 m/s flows over the plate. Find the thicknessof the boundary layer at x = L.Consider a flat plate at zero angle of attack in an airflow at standard sea level conditions (p∞ = 1.01 × 105 N/m2 and T∞ = 288 K). The chord length of the plate (distance from the leading edge to the trailing edge) is 2 m. The planform area of the plate is 40 m2. At standard sea level conditions, μ∞ = 1.7894 × 10−5 kg/(m)(s). Assume the wall temperature is the adiabatic wall temperature Taw. Calculate the friction drag on the plate assuming a turbulent boundary layer for a freestream velocity of (a) 100 m/s, and (b) 1000 m/s.
- In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required to keep a 75 kg person suspended in the air in a horizontal position. The height of this person is 1.7m and the width is 38cm and the front drag coefficient is around 1. Atmospheric pressure and temperature inside the tunnel are Patm = 85kPa and T = 25C, respectively.A 0.25 kg kite with an area of 0.65 mitres squared flies in a 25 km/h wind such that the weightless string makes an angle of 40° relative to the horizontal.The density of air is 1.22 kg/m^3.if the pull on string is 7 N.determine the lift and drag coefficient basee on the kite area. A bicyclist of mass 70 kg supplies 300 W of power while riding into a 3 m/s headwind. The frontal area of the cyclist and bicycle together is 0.36 m^2 , the drag coefficient is 0.88, and you can ignore rolling resistance. Determine the speed of the cyclist (assuming standard atmospheric conditions).