Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5°
Q: Air is flowing past a symmetrical airfoil at an angle of attack of 5°. Is the (a) lift and (b) drag…
A: If an object is placed in a fluid flow, it experiences forces. Say, a body or say an airfoil is…
Q: Calculate the lift and drag coefficiens for a flat plate at a 5◦ angle of attack in a Mach 3 flow.
A: Given data:
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: Name some applications in which a large drag is desired.
A: Drag force is a force acting on a body (moving or stationary)which is present in a moving or…
Q: Calculate lift, drag and (T/W ratio) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a…
A: Given data U∞=500 m/sA=45 m2CD=0.05CL=0.9
Q: Which type of airfoil gives a higher lift? Elaborate the answer
A: Camber of an airfoil refers to the distance between the centre line to the the surface. When the…
Q: Problem 3. Air at 20°C and 1 atm (p= 1.2 kg/m³ and u= 1.8×105 kg/(m-s)) flows at 3 m/s past a sharp…
A: (a) Calculate the Reynolds's number. Re=ρvLμ=1.2311.8×10-5=2×105<5×105so flow is laminar
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: An Aircraft with a drag coefficient of 0.95 and a frontal area of 10 m? is travelling at a Mach…
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Q: Consider a thin, symmetric airfoil at 1.5◦ angle of attack. From the resultsof thin airfoil theory,…
A: The angle of attack is
Q: An Aircraft with a drag coefficient of 0.95 and a frontal area of 10 m2 is travelling at a Mach…
A:
Q: Using supersonic linearized theory, calculate the lift and drag coefficient for a flat plate at 10°…
A:
Q: Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5°…
A: Upper pressure ratio is calculated using P-M expansion theory. Lower pressure ratio is calculated…
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: An Aircraft with a drag coefficient of 0.95 and a frontal area of 10 m2 is travelling at a Mach…
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Q: Consider a NACA 2412 airfoil at an angle of attack of 4 degrees. If the freestream Mach number is…
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Q: What is the effect of increasing the airfoil angle of attack on lift and flight? Brie- explain with…
A: Up to a certain degree, increasing the angle of attack increases lift and produced drag. When…
Q: During a winter day, wind at 55 km/h, 5°C, and 1 atm is blowing parallel to a 4-m-high and 10-m-long…
A: Given data velocity of wind 55 km/hr = 15.27 m/sec height of the wall h = 4m length of the wall L =…
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: Explain how Foilsim determines lift and drag.
A:
Q: Consider a flat plate at zero angle of attack in an airflow at standard sea level conditions (p∞ =…
A: Given data: Sea level conditions: P∞=1.01×105 N/m2, T∞=288K, μ∞=1.7894×10-5 kg/(m.s) Also for air…
Q: A medium-sized jet has a 3.8-m-diameter fuselage and a loaded mass of 85,000 kg. The drag on an…
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Q: Using linearized theory, calculate the lift and drag coefficients for a flat plate at a 5◦ angle of…
A: Given data: The angle of attack, α = 5o. The Mach number, M = 3. Calculate the lift using the…
Q: Study how the lift and drag varies with a change in angle of attack for a flat plate, symmetrical…
A: Validation of the sectional airfoil performance is necessary to test a propeller. This study…
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: es pressure drag on a well designed aerofoil?
A: Given: Pressure drag on a well designed aerofoil.
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: During a winter day, wind at 70 km/h, 5°C, and 1 atm is blowing parallel to a 4-m-high and 15-m-long…
A: Velocity of wind = 70 km/h = 19.444 m/s The pressure of the air = 1 atm Length of the wall = 15m…
Q: is the drag coefficient 2 or 0.2?
A: Yes from figure we can see that drag coefficient at 80000 is 0.2 not 2
Q: Based strictly on your understanding of the flat-plate theoryplus adverse and favorable pressure…
A: From left to right flow, Iniatialy larger pressure gradient but as flow moves past aerofoil lesser…
Q: A light aircraft is flying at a speed of 60 m/s in ISA conditions for an altitude of 2000 m. The…
A: Given data: Calculate the Reynold number as follows:
Q: At subsonic speeds, how do the lift coefficient CL and drag coefficientCD for a wing vary with angle…
A: When the angle of attack increases, the flow separation on the upper surface of the wing becomes…
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 shuttlecock is launched from the ground with an initial speed of 36.9838 m/s at an angle of 9.9728…
A: given information: The initial speed of shuttle cock (u) = 36.9838 m/s angle made by initial…
Q: lift coefficient CL=? with calculated magnitude of lift force from potential flow theory
A: Given that radius of 5 m length of 3 m air having a density ρ=1,2 kg/m3 free-sream speed of 3 m/s…
Q: b) Figure Q1(b) shows a smooth flat plate that is 150 mm wide and 500 mm long placed longitudinally…
A: Drag force: The drag force is the force acting opposite to the direction of fluid flow. Due to its…
Q: An aircraft with symmetric airfoil of wing area 20 m2, flying with velocity 60km/hr experiences lift…
A: Given: Wing area is 20 m2. Velocity of the aircraft is 60 km.hr. Lift coefficient is 0.8.
Q: Determine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying…
A: Introduction: The lift coefficient (CL), a dimensionless coefficient, connects the lift produced by…
Q: How to get more accurate data for lift coefficient (Cl) and drag coefficient (Cd) compared to…
A: Foilsim is the software used to simulate the flow of fluid around various shapes. It displays the…
Q: 4.5 Determine the additive drag for an inlet and a Mach number M₁ of 0.4 at an altitude of 2000 ft.…
A: Given: The inlet area, A = 7000 in^2 = 4.516 m^2 The inlet Mach number, M1 = 0.8 The flying Mach…
Q: How does the construction of a low speed and high-speed aircraft differ? What effects can be…
A: The choice of the airfoil for the airplane wing involves the selection of camber, thickness ratio…
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: Explain
A: given: explain lift force and lift coefficient
Q: Calculate the heat transfer from a 60 cm x 60 cm plate on which air flows at 40⁰C and. The plate…
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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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- Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance from the entrance to the point at which the hydrodynamic boundary layers meet.Consider a flat-plate airfoil at an angle of attack of 6°. TheMach number is Ma∞ = 3.2 and the stream pressure p∞ isunspecified. Calculate the predicted lift and drag coefficientsby (a) shock-expansion theory and (b) Ackeret theory.Consider a flat plate at α = 20◦ in a Mach 20 freestream. Using straightnewtonian theory, calculate the lift- and wave-drag coefficients. Comparethese results with exact shock-expansion theory.
- Calculate the lift and drag coefficiens for a flat plate at a 5◦ angle of attack in a Mach 3 flow.a balloon is 4 m in diameter and contains helium at 125 kpa and 15°c. balloon material and payload weigh 200 n, not including the helium. estimate (a) the terminal ascent velocity in sea-level standard air, (b) the final standard altitude (neglecting winds) at which the balloon will come to rest, and (c) the minimum diameter (< 4 m) for which the balloon will just barely begin to rise in sea-level standard air.Starting from the basic principles, drive an expression to compute the lift coefficient when the free stream Mach number equals (0.8)
- The lift curve for the 4 digit NACA 2421 airfoil is shown in the Figure. Consider a wing with AR = 8, sweep ? = 15 ???, and airplane flies at the Mach number equal to 0.3. The Oswald efficiency span number ?1 = 0.95 Calculate the lift slope for the finite wing. Clearly show the formula and explanations in the solution.A straight-tapered flying-wing aircraft has the following characteristics: span, 20 ft; area, 100 ft2 ; root chord, 6 ft; tip chord, 4 ft; leading-edge sweep angle, 40 deg; sweep angle of line of maximum thickness, 24 deg; and Airfoil NACA 2412. Determine the wing's lift-curve slope and induced drag k value. Assume the flight Mach number is 0.25 in standard sea-level conditions.Consider a rectangular wing with a NACA 23015 airfoil that has a maximum thickness of 2.7 ftand a wing span of 20ft if the freestream density, temperature and mach number are 1.22x10^-3 slugs/ft^3, 444 R and 0.2 respectively. Calculate the lift if the coefficient of lift is 0.8. English unit not metric
- Consider a two-dimensional airfoil that is modelled using potential flow, if the angle of attack is continuously increased, will the airfoil stall? Yes O No Only if the flow is supersonic Only if the Kutta condition is imposedThrust is required to propel an airplane at a fi nite forwardvelocity. Does this imply an energy loss to the system?Explain the concepts of thrust and drag in terms of the fi rstlaw of thermodynamics.For the shown continuously circular (i.e. not parabolic) arc airfoil with sharp corners of each 8 = 5°, at 0° angle of attack with Mo = 3 and assuming steady, two-dimensional flow, calculate the: a) pressure coefficient distribution; b) lift coefficient; c) drag coefficient. Moo 8 ********* 8