A finite wing of area 1.5 ft 2 and aspect ratio of 6 is tested in a subsonic wind tunnel at a velocity of 130 ft/s at standard sea-level conditions. At an angle of attack of −1°, the measured lift and drag are 0 and 0.181 lb, respectively. At an angle of attack of 2°, the lift and drag are measured as 5.0 and 0.23 lb, respectively. Calculate the span efficiency factor and the infinite-wing lift slope.

Q: What will be the percentage decrease in power density for a 15 m/s wind at an elevation of 1200 m…

A:

Q: A bicyclist of mass 70 kg supplies 300 W of power while riding into a 3 m/s headwind. The frontal…

A: Given data: m=70 kgP=300 Wvw=3 m/sA=0.36 m2CD=0.88 Need to determine the speed of the cyclist.

Q: An aircraft has a total mass of (1.26x10^2) kg and a wing area of (2.3000x10^1) m². It operated with…

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Q: What will be the percentage decrease in power density for a 15 m/s wind at an elevation of 1200 m…

A:

Q: A sphere (Cd = 0.2) 1 ft in diameter travels at 100 ft/sec in standard atmospheric air. What is the…

A:

Q: An aircraft has a total mass of (1.14x10^2) kg and a wing area of (2.4000x10^1) m² It operated with…

A: Given Data: Drag coefficient, Cd=0.1 The density of air, 1.2 kg/m3

Q: Sir Isaac Newton measured the speed of sound by timing the difference between seeing a cannon's puff…

A: Distance d=5.4mi 0c=273.15k To find the temperature in 0c if the time difference is 24.3s

Q: An infinitely thin flat plate is operating at a given freestream Mach number of 2.4 where ambient…

A: Mach number = 2.4 Ambient pressure=0.53 atm Angle of attack=4 Required: Lift to drag ratio

Q: Using supersonic linearized theory, calculate the lift and drag coefficient for a flat plate at 10°…

A: To find: The lift and drag coefficient for a flat plate at mach 3 flow and mach 4 flow. Given: The…

Q: In the test section of a high-speed subsonic wind tunnel operating at Mach number of 0.75, a NACA…

A: Solution: Given Data: M=0.75Cc,L=0.7   To Find: (a) The angle of attack, α? (b) Equivalent…

Q: What will be the percentage decrease in power density for a 15 m/s wind at an elevation of 1200 m…

A:

Q: In a laboratory, the drag forces that are generated on vehicles that carry are being studied…

A: Given data: Projected frontal area = 2 m2Drag force = 300 Nvelocity of air moving = 27 m/s T…

Q: power available at sea-level PA; 0 = 140 kW wingspan b = 11 m wing area S = 16 m2 zero-lift drag…

A: Given data: Power available at sea-level: PA;0 = 140 kW = 140000 W Wingspan: b = 11 m Wing area: S =…

Q: An aircraft has a total mass of (1.26x10^2) kg and a wing area of (1.800x10^1) m². It operated with…

A: Given data:

Q: = 175 ft², aspect ratio of wing = 6.5. The maximum available thrust from the aircraft engine a…

A:

Q: An infinitely thin flat plate is operating at a given freestream Mach number of 2.4 where ambient…

A: Mach number = 2.4 Ambient pressure=0.53 atm Angle of attack=4 Required: Lift to drag ratio

Q: An aircraft has a total mass of (1.48x10^2) kg and a wing area of (2.0000x10^1) m². It operated with…

A: For the given situation, we first need to obtain the trust required and the take-off velocity for…

Q: What will be the percentage decrease in power density for a 15 m/s wind at an elevation of 1200 m…

A:

Q: 16. The flow in a compressor cascade test has an angle of 60° at inlet and of 30° at outlet. The…

A: Givenα1=60°α2=30°sD=0.8

Q: What is the formula and variables in finding the air drag of a motorcycle?

A: Given question: What is the formula and variables in finding the air drag of a motorcycle. The given…

Q: Consider a solid iron sphere entering the earth's atmosphere at 13 km/s (slightly above es- cape…

A: (a) To find: The altitude at which maximum declaration occurs. Given: The speed of solid iron is…

Q: An infinitely thin flat plate is operating at a given freestream Mach number of 2.4 where ambient…

A: Mach number = 2.4 Ambient pressure=0.53 atm Angle of attack=4°

Q: Task 3: An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The…

A: Given data:- Span length of air foil  S = 36 m Aspect ratio = 10 Speed, u = 150 m/s Altitude, h =…

Q: What will be the percentage decrease in power density for a 15 m/s wind at an elevation of 1200 m…

A: The density of air at 1200 meters and 25 degrees celsius, and standard density of air is

Q: 2. Taking off on a dry cement runway, to minimize the impact of aerodynamics on the acceleration,…

A: Ans: Option(D) 1.7o

Q: A three-blade propeller of a diameter of 1.5 m has a rotational speed is 60 Hz, the activityfactor…

A: The objective of the question is to calculate the required thrust to weight ratio for an aircraft to…

Q: M = 3.0 60 A = 40° ة و 6 = 20°

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Q: A horizontal-axis wind turbine with rotor 80m in diameter is 35% efficient in 18m/s wind at 0.977…

A: The power available in the wind can be calculated using the formula:…

Q: power available at sea-level PA; 0 = 140 kW wingspan b = 11 m wing area S = 16 m2 zero-lift drag…

A: To Find : The maximum rate of climb at sea level and at altitude 5000 m Given : The Power available…

Q: ceilings

A: Sea level maximum R/C condition Lift coefficient for maximum rate of climb CL=-TW+TW2+12CD,OK2K…

Q: An aircraft has a total mass of (1.18x10^2) kg and a wing area of (1.4000x10^1) m2. It operated with…

A:

Q: An aircraft has a gross weight of 140000lb, wing area 2.333ft², maximum thrust 37800lb, CDo = 0.018,…

A: To plot the drag-to-weight ratio (D/W) and the maximum thrust-to-weight ratio (T/W) as a function of…

Q: A 1500 kg electric vehicle travels along an asphalt roadway with a 5° grade at 100 km/h and a…

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Q: n aircraft has the drag polar, C_d=0.015+0.05C_l^2 For a lift coefficient of 0.5, find the value of…

A: Given:Drag coefficient, Cd=0.015+0.05ClLift coefficient, Cl=0.5

Q: The Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as: Cp…

A: Given: W = 2300 lb CD = 0.027 + Cl2/32.787

Q: Experiments were conducted in a wind tunnel with a wind speed of 16.66 m/sec on a flat plate having…

A: Given, Wind speed, V=16.66m/s Area, A=2.25×104cm2 Density, ρ=1.2kg/m3 Coefficient of lift, CL=0.25…

Q: An aircraft has a total mass of (8.800x10^1) kg and a wing area of (3.00x10^1) m2. It operated with…

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Fluid Dynamics

The study of the flow of gases and liquids, usually in and around solid surfaces, is known as fluid dynamics in physics and engineering. Fluid dynamics, for example, can be used to evaluate the movement of air through an airplane wing or the surface of a vehicle. It can also be used in ship design to increase the speed at which ships pass through water.