For a normal shock, the downstream flow is always subsonic. For an oblique shock, what can be said about the downstream flow?
Explanation
Unlike a normal shock which always results in subsonic flow, an oblique shock has two possibilities. A 'weak' oblique shock (smaller angle, smaller losses) can have a supersonic downstream state, while a 'strong' oblique shock (larger angle, larger losses) always results in a subsonic downstream state.
Other questions
What component of the flow velocity remains constant across an oblique shock wave?
For a given upstream Mach number and deflection angle, the cubic equation for the shock angle (θ) can yield multiple solutions. What is the 'strong solution' characterized by?
Under what condition does a detached shock form in front of a wedge instead of an attached oblique shock?
In the cubic equation used to find the shock angle (x = sin squared theta), what is the physical meaning when the discriminant D is greater than 0?
How is the normal component of the upstream Mach number (M1n) related to the upstream Mach number (M1) and the shock angle (theta)?
What is the primary conceptual difference in the analysis of supersonic flow over an infinite wedge versus a cone?
What is a major practical application of designing with a series of weak oblique shocks, as described in the chapter?
According to the stability analysis described in the appendix, why is a weak oblique shock considered stable?
What does the Rankine-Hugoniot relation describe for an oblique shock?
For an upstream Mach number (Mx) of 2.0, what is the maximum possible deflection angle (delta_max) in degrees?
What is the relationship between the deflection angle (delta) and the shock angle (theta) for very large upstream Mach numbers (M1 approaches infinity) and small angles?
In Example 14.2, air flows at Mach 4 towards a wedge with an angle of 20 degrees. What is the downstream Mach number for the weak shock solution (Myw)?
According to the discussion on zero inclination, what prevents the continuous formation of Mach waves from a perfectly smooth, straight wall?
In the analysis of a detached shock around a round-tip bullet, what is the flow condition in Zone A, the region directly in front of the body's stagnation point?
What is the pressure ratio (P2/P1) across an oblique shock if the upstream Mach number M1 is 3.0 and the shock angle theta is 30 degrees? Use k=1.4.
In the context of Mach reflection, as shown in Figure 14.13, what happens at the intersection of the two oblique shocks?
If air (k=1.4) at Mach 2.5 is deflected by a wedge, what is the Mach number of the flow downstream of the shock (My) if the deflection is the maximum possible?
What does Prandtl's relation for an oblique shock connect?
For a given upstream Mach number M1, what is the theoretical minimum possible shock angle (theta)?
In Example 14.10, an incident shock from a 15-degree deflection at Mach 4 strikes a wall, creating a reflected shock. What is the Mach number upstream of this second (reflected) shock?
Why does the temperature change across an oblique shock even though the tangential velocity component U_t is constant?
If an oblique shock has a shock angle (theta) of 30 degrees and the deflection angle (delta) is 10.51 degrees, what is the upstream Mach number (M1) according to the data in Example 14.11?
What is the key takeaway from Example 14.4, which compares a single normal shock at M=2.0 with a two-stage oblique shock system?
According to the table of maximum values for oblique shock (k=1.4), what is the maximum shock angle (theta_max) for an upstream Mach number (Mx) of 1.4?
What is the 'close view' of an oblique shock, as described in section 14.4.7?
If a supersonic flow at M=3.5 creates a detached shock in front of a wedge, what is the Mach number immediately behind the normal portion of the shock?
According to the table of maximum values, as the upstream Mach number (Mx) increases from 1.1 to 10.0, what is the general trend of the maximum possible deflection angle (delta_max)?
What is the explicit equation for the downstream Mach number squared (M2 squared) given M1 and the shock angle theta?
For a supersonic flow at M=2.88 and a Mach angle of 34 degrees, what is the deflection angle (delta) in degrees?
In Example 14.13, which describes a flow with two different deflection angles on opposing walls, what physical quantities must be equal across the resulting slip plane?
What is the relationship for the density ratio (rho2/rho1) across an oblique shock?
For a very weak oblique shock, where the deflection angle delta is very small, the shock angle theta approaches what value?
According to the analysis of a finite wedge in Section 14.4.5, where is the 2D oblique shock theory most accurate?
If a cone with a half-angle of 14.43 degrees in a supersonic flow creates a shock with an angle of 30.099 degrees, what was the upstream Mach number M1, based on the data in Example 14.3?
What is the temperature ratio (T2/T1) for an oblique shock with M1=2.88 and theta=34.0 degrees?
Why is the maximum deflection angle for a Prandtl-Meyer expansion wave much larger than for an oblique shock at the same high Mach number?
Given an upstream Mach number M1 and a shock angle theta, the deflection angle delta is:
In Example 14.2, when the wedge angle is 20 degrees and M1=4.0, what is the shock angle (theta_w) for the weak solution in degrees?
For a perfect gas with k=1.4, what is the total stagnation pressure ratio (P0y/P0x) for a normal shock at M=5.0?
If a flow at M=1.7498 turns through a weak oblique shock with a deflection of 7 degrees, what is the stagnation pressure ratio (P0y/P0x) from the data in Example 14.4?
What does the deflection angle, delta, represent in the context of an oblique shock?
When is the analysis for upstream Mach number M1 and deflection angle delta the most complicated?
What is the static pressure ratio (Py/Px) after a normal shock for an upstream Mach number of 3.5?
In the cubic equation x^3 + a1*x^2 + a2*x + a3 = 0 for the shock angle, what does the variable x represent?
Why does the text state that the thermodynamically unstable root of the shock angle cubic equation is 'unrealistic' for steady-state analysis?
Based on Example 14.9, what is the maximum static pressure ratio (Py/Px) that can be obtained across a WEAK oblique shock for M1=2.5?
What happens to the total energy of the flow as it passes through an oblique shock wave?
If a flow has an upstream Mach number M1 of 5.0 and the shock angle theta is 30 degrees, what is the downstream Mach number for the weak solution (Myw) based on the data in Example 14.12?
What is the primary reason that a normal shock is considered a 'special case' of an oblique shock?