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.Air at 1000C flows at an inlet velocity of 2 m/s between two parallel flat plates spaced 1 cm apart. Estimate the distance from the entrance to the point where the 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 metricConsider 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.