Question

Question 4 Consider a flying object as sketched in Figure Q4. The freestream Mach number is $M_\infty = 3.0$ at an altitude where $p_\infty = 27,000$ Pa, $T_\infty = 224$ K, $\rho_\infty = 0.4$ kg/m$^3$. (a) Sketch the shock and expansion wave patterns. (4 marks) (b) Determine the pressure in Sections I, II and III using the Prandtl-Meyer theory. (11 marks) (c) Determine the pressure in Sections I, II and III using the linear theory. (6 marks) (d) Comment on the results of (b) and (c) in Section II in relation to the freestream condition. (2 marks) (e) Comment on the result of (c), whether the calculated pressure in Section III is realistic. (2 marks) $M_\infty$ 0.3 m 0.9 m Section I 0.5 m Section II 0.6 m Section III Figure Q4

          Question 4
Consider a flying object as sketched in Figure Q4. The freestream Mach number is $M_\infty = 3.0$ at an
altitude where $p_\infty = 27,000$ Pa, $T_\infty = 224$ K, $\rho_\infty = 0.4$ kg/m$^3$.
(a) Sketch the shock and expansion wave patterns.
(4 marks)
(b) Determine the pressure in Sections I, II and III using the Prandtl-Meyer theory.
(11 marks)
(c) Determine the pressure in Sections I, II and III using the linear theory.
(6 marks)
(d) Comment on the results of (b) and (c) in Section II in relation to the freestream condition.
(2 marks)
(e) Comment on the result of (c), whether the calculated pressure in Section III is realistic.
(2 marks)
$M_\infty$
0.3 m
0.9 m
Section I
0.5 m
Section II
0.6 m
Section III
Figure Q4

Question 4
Consider a flying object as sketched in Figure Q4. The freestream Mach number is M∞ = 3.0 at an
altitude where p∞ = 27,000 Pa, T∞ = 224 K, ρ∞ = 0.4 kg/m^3.
(a) Sketch the shock and expansion wave patterns.
(4 marks)
(b) Determine the pressure in Sections I, II and III using the Prandtl-Meyer theory.
(11 marks)
(c) Determine the pressure in Sections I, II and III using the linear theory.
(6 marks)
(d) Comment on the results of (b) and (c) in Section II in relation to the freestream condition.
(2 marks)
(e) Comment on the result of (c), whether the calculated pressure in Section III is realistic.
(2 marks)
M∞
0.3 m
0.9 m
Section I
0.5 m
Section II
0.6 m
Section III
Figure Q4

Added by Derek A.

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