Aerospace Engineering
GATE AE topic:compressible-flows PYQs
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How to practice topic:compressible-flows
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Questions 1–10 of 41. Imported answers require independent review unless marked reviewed.
Question 21
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In the figure shown below, the flow at the nozzle exit is _______.
Your answerChoose one option.
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A flow is steady, inviscid and one-dimensional, with no shaft work or body forces. Which of the following is/are possible under the given conditions?
Your answerSelect all correct options. You can choose more than one.
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Consider a centered Prandtl-Meyer expansion fan at a
corner in a Mach 1.78 air flow, as shown in the figure below. The angle
(see figure) made by the ending wave of the fan with respect to the incoming stream is ________ degrees (rounded off to 1 decimal place).An excerpt from the table of Prandtl-Meyer function for air is provided below.
M | [deg] | M | [deg] | M | [deg] |
|---|---|---|---|---|---|
1.72 | 18.40 | 1.82 | 21.30 | 1.92 | 24.15 |
1.74 | 18.98 | 1.84 | 21.88 | 1.94 | 24.71 |
1.76 | 19.56 | 1.86 | 22.45 | 1.96 | 25.27 |
1.78 | 20.15 | 1.88 | 23.02 | 1.98 | 25.83 |
1.80 | 20.73 | 1.90 | 23.59 | 2.00 | 26.38 |
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A Mach 1.5 air flow enters a round duct of length 20 cm and diameter 3 cm. If the flow exits with Mach number 1.1, the average Fanning friction factor
of the duct is ________
(rounded off to 1 decimal place).An excerpt from the Fanno flow table for air is given below.
| 1.1 | 1.2 | 1.3 | 1.4 | 1.5 | 1.6 |
|---|---|---|---|---|---|---|
| 99.35 | 336.4 | 648.3 | 997.4 | 1361 | 1724 |
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In a fluid flow, Mach number is an estimate of _____.
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An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature and density are 57 kPa, 259 K and 0.77 kg/m
, respectively. The speed of the aircraft (
) is 230 m/s. Gas constant
J/kg/K, and specific heat ratio
. If the stagnation pressure is
, and static pressure is
, the value of
is
(rounded off to two decimal places).Log in to check the answer
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A supersonic stream of an ideal gas at Mach number
is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is
and the specific heat ratio is
. The pressure coefficient on the ramp surface is
(rounded off to two decimal places). 
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A perfect gas flows through a frictionless constant-area duct with heat addition. The inlet conditions are as follows: pressure 100 kPa, density 1 kg/m
, and velocity 100 m/s. At a particular downstream location, the gas velocity is 200 m/s. The static pressure at the downstream location is
kPa (answer in integer).Log in to check the answer
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The mass flow rate in a supersonic wind tunnel is 2 kg/s when the stagnation pressure and stagnation temperature are 1 MPa and 800 K, respectively. If the stagnation pressure and stagnation temperature are changed to 3 MPa and 200 K, the mass flow rate in the tunnel changes to
kg/s (answer in integer).Log in to check the answer
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Consider a steady, isentropic, supersonic flow (Mach number M > 1) entering a Convergent-Divergent (CD) duct as shown in the figure. Which one of the following options correctly describes the flow at the throat?
Your answerChoose one option.
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