During the entry of the Apollo space vehicle into the Earth's atmosphere, the Mach number at a given point on the trajectory was M = 38 and the atmospheric temperature was 270 K. Calculate the temperature at the stagnation point of the vehicle, assuming a calorically perfect gas with γ = 1.4. Do you think this is an accurate calculation? If not, why? If not, is your answer an overestimate or underestimate?

The temperature at stagnation point is 78246K. The answer is an overestimate of the actual value.

Explanation:

Given:

Mach number, M = 38

Atmospheric temperature, Tₐ = 270K

γ = 1.4

Temperature at the station point, Tₓ = ?

We know,

Tₓ = 270 X [ 1 + (38*38) X (1.4-1) /2]

Tₓ = 270 X [ 1 + 577.6/2]

Tₓ = 270 X [1 + 288.8]

Tₓ = 270 X 289.8

Tₓ = 78246K

Therefore, the temperature at stagnation point is 78246K which seems to be inaccurate because the assumption of a calorically perfect gas holds good up to M = 5.

The answer is an overestimate of the actual value.

the equation above shows how temperature f, measured in degrees fahrenheit, relates to a temperature c, measured in degrees celsius. based on the equation, which of the following must be true?

a temperature increase of 1 degree fahrenheit is equivalent to a temperature increase of

5

9

degree celsius.

a temperature increase of 1 degree celsius is equivalent to a temperature increase of 1.8 degrees fahrenheit.

a temperature increase of

5

9

degree fahrenheit is equivalent to a temperature increase of 1 degree celsius.

a) i only

b) ii only

c) iii only

d) i and ii only

answer:

explanation:

assault rifle is a rapid-fire, magazine-fed rifle designed for military use. it is a shoulder-fired weapon that allows the shooter to select between semi-automatic (requiring you pull the trigger for each shot), fully automatic (hold the trigger and the gun continuously fires) or three-shot-burst modes.