Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 12, Problem 12.2P
For the conditions of Problem 12.1, calculate the pressures (in the form of
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Chapter 12 Solutions
Fundamentals of Aerodynamics
Ch. 12 - Using the results of linearized theory, calculate...Ch. 12 - For the conditions of Problem 12.1, calculate the...Ch. 12 - Consider a diamond-wedge airfoil such as shown in...Ch. 12 - Equation (12.24). from linear supersonic theory....Ch. 12 - Consider a flat plate at an angle of attack in an...Ch. 12 - Consider a flat plate at an angle of attack in a...Ch. 12 - Using the same flight conditions and the same...Ch. 12 - The result from Problem 12.6 demonstrates that...
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- Calculate the quality x and temperature Tsat when pressure p is 1000 KPa and U=2950 KJ/Kg.arrow_forwardDetermine the other properties of the steam for the following conditions T= 320°C, u= 2000 kJ/kg-K P= 1.42 Mpa, T=355 °Carrow_forward6. 308 Moles of He has pressurized to 17167kPa at 20*Ccylinder 20cm diameter at 1m^3 20*C water bath at sea levelwhat is the initial height of the piston before weights are placed on the piston How much mass is needed before achieving desired pressure How far does the piston move after weights are put on the pistonarrow_forward
- Determine the solution of the inviscid Burgers' equation for the double-shock pro- file given by u₁ = 1.0, u₂ = 0.5, and u3 = 0. Compute this solution using MacCormack scheme and the Godunov method. What is the analytic solution for this set of ini- tial conditions? Compare your numerical calculation with the analytical solution.arrow_forwardDerive a formula for the bulk modulus of an ideal gas, withconstant specifi c heats, and calculate it for steam at 300° Cand 200 kPa. Compare your result to the steam tables.arrow_forwardUsing the Image below solve the following two questions, AND ONLY SOLVE FOR i and iii a.Determine The total pressure loss in the final state, after the 20 degree turn, for i and iii. (I'd also like to confirm for ii that the total pressure loss is 0?) b.Determine the Mach number in the final state. For which geometry is this highest? ( For ii it is 2.12) ALSO USE THE OTHER PICTURE WITH TABLES TO HELP YOU ANSWERarrow_forward
- .........TheGaugePressure 0f the air in an aut0m0bile tire is 25psi, and assuming the ambient atm0sphericPressure is38psi. Express the_abs0lute_pressure_in the tire in bars.arrow_forwardThe pressure of steam 400 C and u = 2949 kJ/kg is most nearlyarrow_forward4-A round-nosed projectile travels through air at a temperature of -15°C and a pressure of 1.8 ×10 pa. The stagnation projectile is measured at pressure on the nose of the 2.1 x 105 2 (a) At what speed (m/s) is the projectile traveling? pro pa. Svation (b) What is the temperature on the projectile's nose? (c) Now assume that the nose tip is shaped like a cone. What is the maximum cone angle for the shock to remain attached?arrow_forward
- (b) An experimental balloon filled with helium is equipped with meteorological instruments is released to the atmosphere from sea level. Measurement data was analysed to derive the linear temperature lapse rate up to high altitudes above sea level. The lapse rate was found to be equal to 0.0065 K/m. Estimate the altitude of the balloon above sea level when the atmospheric pressure is equal to 60 kPa. Atmospheric temperature and pressure at sea level may be assumed to be equal to 15°C and 101 kPa. Characteristic gas constant is 287J/kgK.arrow_forward-NES Start from first principle to show that, for perfect gas the velocity of the sound is given by: C= √KRTarrow_forwardUsing the Image below solve the following two questions, AND ONLY SOLVE FOR i and iii a.Determine The total pressure loss in the final state, after the 20 degree turn, for i and iii. (I'd also like to confirm for ii that the total pressure loss is 0?) b.Determine the Mach number in the final state. For which geometry is this highest? ( For ii it is 2.12)arrow_forward
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