AERO GATE TOPPER
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×Basic Aerodyanamics and Fluid mechanics
AERO GATE TOPPER
1. Calculate the lift coefficient (Cl) for a thin airfoil at a 5-degree angle of attack, considering a subsonic flow. Assume 2D flow and ideal conditions. (in 2 decimal)
2. Which airfoil type has the highest maximum lift coefficient (Clmax) under subsonic conditions?
3. For a supersonic flow, determine the shock wave angle in degrees when the Mach number is 2.5 and the deflection angle is 15 degrees.(in 1 decimal)
4. Select the correct properties of a turbulent boundary layer:
5. Calculate the specific thrust (in kN/kg) of a turbojet engine operating at a Mach number of 0.8 at an altitude of 10 km.assuming temperature at 10km=-50 °C and exhaust velocity around 2160 km/hr. (in 4 decimal)
6. Which of the following methods is used to reduce induced drag on an aircraft wing?
7. Determine the Prandtl number for an airfoil experiencing boundary layer transition from laminar to turbulent flow at an altitude of 15,000 meters. (Assuming at altitude 15,000 meters propertiesof air Dynamic viscosity (μ) is 1.42 x 10^-5 kg/(m·s), Specific heat at constant pressure (C_p) is 1005 J/(kg·K) and Thermal conductivity (k) is 0.0227 W/(m·K))
8. Which of the following methods can be used to delay boundary layer separation on an airfoil?
9. Calculate the drag coefficient (Cd) of a flat plate at zero angle of attack in incompressible flow for a Reynolds number of 1 x 10^6. (in 3 decimal)
10. Which factors increase the wave drag in a transonic aircraft?
11. Calculate the critical Mach number for an airfoil with a thickness-to-chord ratio of 12%. (in 2 deicmal)
12. In compressible flow, the Prandtl-Glauert transformation is used to:
13. Select the correct statements regarding supersonic flow over a wedge:
14. Calculate the lift coefficient (Cl) for an aircraft with a lift of 50,000 N, a wing area of 40 m², and a dynamic pressure of 600 N/m². (in 2 decimal)
15. In high-speed flows, the purpose of a converging-diverging nozzle is to:
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