Answer:
An aircraft, flying in the vicinity of 18,000 ft altitude from west to east over the US at 12 Z today, will __LOSE___ altitude if the altimeter is not corrected
Answer:
2.06 m³/s
Explanation:
diameter of pipe, d = 0.81 m
diameter of constriction, d' = 0.486 m
radius, r = 0.405 m
r' = 0.243 m
density of oil, ρ = 821 kg/m³
Pressure in the pipe, P = 7970 N/m²
Pressure at the constriction, P' = 5977.5 N/m²
Let v and v' is the velocity of fluid in the pipe and at the constriction.
By use of the equation of continuity
A x v = A' x v'
r² x v = r'² x v'
0.405 x 0.405 x v = 0.243 x 0.243 x v'
v = 0.36 v' .... (1)
Use of Bernoulli's theorem

7970 + 0.5 x 821 x 0.36 x 0.36 x v'² = 5977.5 + 0.5 x 821 x v'² from (i)
1992.5 = 357.3 v'²
v' = 5.58 m/s
v = 0.36 x 5.58
v = 2 m/s
Rate of flow = A x v = 3.14 x 0.405 x 0.405 x 2 x 2 = 2.06 m³/s
Thus the rate of flow of volume is 2.06 m³/s.
The acceleration is given as:
a = g sin(30°) where g is the gravitational acceleration
For g = 10 m/s^2, we get
a = 10 sin(30°) = 10 * 1/2 = 5 m/s^2
Answer: Part 1: Propellant Fraction (MR) = 8.76
Part 2: Propellant Fraction (MR) = 1.63
Explanation: The Ideal Rocket Equation is given by:
Δv = 
Where:
is relationship between exhaust velocity and specific impulse
is the porpellant fraction, also written as MR.
The relationship
is: 
To determine the fraction:
Δv = 

Knowing that change in velocity is Δv = 9.6km/s and
= 9.81m/s²
<u>Note:</u> Velocity and gravity have different measures, so to cancel them out, transform km in m by multiplying velocity by 10³.
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<u>Part 1</u>: Isp = 450s

ln(MR) = 
ln (MR) = 2.17
MR = 
MR = 8.76
<u>Part 2:</u> Isp = 2000s

ln (MR) = 
ln (MR) = 0.49
MR = 
MR = 1.63