Comp Aero Day 1-3
Compressible Aerodynamics Quiz
Test your knowledge and understanding of compressible aerodynamics with our comprehensive quiz designed for students, engineers, and enthusiasts alike.
With 28 challenging questions covering topics such as shockwaves, nozzle flows, and supersonic stability, you'll deepen your comprehension and enhance your skills.
- Multiple-choice format
- Fits various expertise levels
- Instant feedback on your performance
As temperature increases in a gas, viscosity
Increases
Decreases
For adiabatic flow, _______ is constant
Total pressure
Total temperature
Mach number
All of the above
For isentropic flow, _______ is constant
Total temperature
Total pressure
Total density
All of the above
Across a shockwave, _______ increases
Velocity
Mach
Total pressure
Static pressure
Flow behind a normal shock is
Subsonic
Sonic
Supersonic
For the same mach number and half angle
The shock is closer to a cone
The shock is closer to a wedge
They are the same
Across an expansion, total pressure
Increases
Decreases
Stays the same (it's isentropic!)
For supersonic flow, as the cross sectional area decreases, Mach number:
Increases
Decreases
What is the significance of A/A*
It's the ratio between current and maximum area
It's the ratio between the inlet and exit
It's the ratio between a given area and the area that would result in choked (M=1) flow
What is the relationship between velocity and density
As one increases, the other increases always
As one increases, the other decreases for supersonic flow only
As one increases, the other decreases always
Who was prandtl's wife?
One of two sisters, he didn't care which
His cousin
Gertrude Foppl
What phenomenon is responsible for drag over a supersonic inviscid airfoil
Drag divergence
Wave drag
Parasite drag
Pressure drag
What is the weakest type of shock
Normal shock
Oblique shock
Mach wave
Expansion fan
Where is the center of pressure for a supersonic airfoil
Quarter chord
Half chord
C.G.
Increasing a supersonic airfoils thickness increases:
Lift
Drag
Both
What is critical mach number
The fastest Mach an aircraft can go
The Mach number when flow is supersonic everwhere
The first Mach number where there is sonic flow at one point on the aircraft
How can you increase Mcrit
Thinner wings
Swept wings
Slender leading edge
Supercritical airfoil
All of the above
Flow behind an oblique shock is
Sonic
Supersonic and faster
Subsonic
Supersonic and slower
What happens when supersonic flow turns away from itself
Separation
Oblique shock
Normal shock
Expansion fan
As nozzle exit pressure decreases, in what order does the flow change
Under expanded (expansion fans in wake), ideally expanded (no shocks or expansions), over expanded (oblique shocks in wake), normal shock at exit, normal shock in nozzle
Normal shock in nozzle, normal shock at exit, overexpanded (oblique shocks in wake), ideally expanded (no shocks or waves), under expanded (expansion fans in wake)
Under expanded (expansion fans in wake), ideally expanded (no shocks or expansions), over expanded (oblique shocks in wake), sonic flow at throat, subsonic flow everwhere
Which design feature does NOT improve supersonic stability and control
Large vertical surfaces
Fully moving control surfaces
Drooped wing tips
Increased wing area
Where is information propagated upstream over a supersonic wing
Everywhere
Nowhere
Inside the Mach cone
To increase total pressure recovery in an inlet
More shocks is better
Fewer shocks is better
What are challenges of hypersonics
Strong entropy gradients
Viscous shock layer
Shock shock interactions
Stuff melts
All of the above
What happens to total temperature across a shock
Increases
Stays the same
Decreases
What happens to temperature across a shock
Increases
Stays the same
Decreases
What happens to pressure across an expansion fan
Increases
Decreases
Stays the same
What happens to entropy across a shock
Increases
Decreases
Stays the same (it's isentropic!)
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