1
GATE ME 2026
MCQ (Single Correct Answer)
+1
-0

Bernoulli's equation CANNOT be applied between

A

any two arbitrary points in the flow field for steady incompressible rotational flow

B

any two arbitrary points in the flow field for steady incompressible irrotational flow

C

any two points along a streamline for steady incompressible flow

D

any two points along a streamline for steady incompressible rotational flow

2
GATE ME 2025
MCQ (Single Correct Answer)
+1
-0.33

Consider two identical tanks with a bottom hole of diameter $d$. One tank is filled with water and the other tank is filled with engine oil. The height of the fluid column $h$ is same in both the cases. The fluid exit velocity in the two tanks are $V_1$ and $V_2$. Neglecting all losses, which one of the following options is correct?

GATE ME 2025 Fluid Mechanics - Fluid Dynamics Question 5 English
A
$V_2>V_1$
B
$V_2=V_1$
C
$V_2
D
Insufficient data to definitively conclude the relationship between $V_1$ and $V_2$.
3
GATE ME 2025
MCQ (Single Correct Answer)
+1
-0.33
In a laboratory experiment using a scaled down model to measure scour at a bridge pier, the Froude number is important. The ratio of the prototype length to the model length is 100 . If the velocity of the model is $1 \mathrm{~m} \mathrm{~s}^{-1}$, the velocity (in $\mathrm{m} \mathrm{s}^{-1}$ ) of the prototype is
A
0.1
B
1
C
10
D
100
4
GATE ME 2023
MCQ (Single Correct Answer)
+1
-0.33

Consider an isentropic flow of air (ratio of specific heats = 1.4) through a duct as shown in the figure.

The variations in the flow across the cross-section are negligible. The flow conditions at Location 1 are given as follows:

๐‘ƒ1 = 100 kPa, ๐œŒ1 = 1.2 kg/m3 , ๐‘ข1= 400 m/s

The duct cross-sectional area at Location 2 is given by A2 = 2A1, where A1 denotes the duct cross-sectional area at Location 1. Which one of the given statements about the velocity ๐‘ข2 and pressure ๐‘ƒ2 at Location 2 is TRUE? 

GATE ME 2023 Fluid Mechanics - Fluid Dynamics Question 12 English
A
๐‘ข2 < ๐‘ข1 , ๐‘ƒ2 < ๐‘ƒ1
B
๐‘ข2 < ๐‘ข1 , ๐‘ƒ2 > ๐‘ƒ1
C
๐‘ข2 > ๐‘ข1 , ๐‘ƒ2 < ๐‘ƒ1
D
๐‘ข2 > ๐‘ข1 , ๐‘ƒ2 > ๐‘ƒ1

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Turbo Machinery