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A high-speed missile is traveling at Mach 3 at standard sea level. What is its velocity in miles per hour?

Short Answer

Expert verified
The missile's velocity is 2283 mph.

Step by step solution

01

Understanding Mach and Sea Level Conditions

Mach number is a dimensionless unit representing the ratio of the speed of an object to the speed of sound in the surrounding medium. At standard sea level, the speed of sound in air is approximately 761 miles per hour.
02

Calculate the Velocity

Given that the missile is traveling at Mach 3, it means it's traveling three times the speed of sound. Therefore, to find the velocity in miles per hour (mph), we multiply the Mach number by the speed of sound at sea level: \[ \text{Velocity (mph)} = 3 \times 761 \text{ mph} = 2283 \text{ mph} \]

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Key Concepts

These are the key concepts you need to understand to accurately answer the question.

Speed of Sound
The concept of the speed of sound is quite fascinating. It refers to how quickly sound waves travel through a medium, like air. At sea level, where the air’s density and pressure are relatively high, this speed is approximately 761 miles per hour. The speed of sound can vary based on factors such as temperature and altitude. For instance, at higher altitudes, where the air is thinner, sound travels slower. This is why the speed is standardized at sea level to provide a consistent reference point.

Sound travels as a wave of pressure, and its speed is influenced by the medium’s properties. Heavier or more rigid media enable sound to travel faster whereas in air, the speed is dependent on pressure and temperature. When studying problems involving the speed of sound, like calculating the velocity of a missile, it's crucial to note the conditions under which this speed is measured to ensure accuracy in computations.
Velocity Calculation
Calculating velocity is a straightforward process once you know the key components. Velocity is the speed of an object in a particular direction. For an object traveling at Mach speed, such as a missile, this calculation becomes simpler by the definition of the Mach number.

The Mach number is essentially the ratio of the object's speed to the speed of sound in that medium. If a missile is traveling at Mach 3, it means its velocity is three times the speed of sound. Thus, calculating its velocity involves a simple multiplication:
  • Determine the speed of sound at your reference condition (like sea level, where it's 761 mph)
  • Multiply this speed by the Mach number
This formula gives us a velocity in mph that aligns with the conditions at which the speed of sound is evaluated. Other environments or conditions could alter this value, so always keep context in mind.
Sea Level Conditions
Understanding sea level conditions is vital for accurately assessing phenomena dependent on atmospheric conditions, like the speed of sound. Sea level refers to the average level of the ocean's surface, used as a standard in measuring elevations and depths on Earth.

Conditions at sea level are characterized by specific atmospheric pressure and temperature standards. These conditions directly affect how sound moves through the air. At sea level, the air is denser and holds sound waves more efficiently, which is why the standard speed of sound is set at 761 miles per hour under these conditions.
  • Standard sea level temperature is around 15 degrees Celsius (59 degrees Fahrenheit)
  • At this temperature, the speed of sound becomes an ideal reference for calculations involving vehicles, like planes or missiles
It’s important when using standard values, like the speed of sound, to adjust calculations if the conditions vary from these reference points, such as higher altitudes or different atmospheric compositions.

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Most popular questions from this chapter

Consider the incompressible flow of water through a divergent duct. The inlet velocity and area are \(5 \mathrm{ft} / \mathrm{s}\) and \(10 \mathrm{ft}^{2}\), respectively. If the exit area is 4 times the inlet area, calculate the water flow velocity at the exit.

The wing of the Fairchild Republic A-10A twin-jet close-support airplane is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of \(17.5 \mathrm{~m}\) and a chord (the length parallel to the flow direction) of \(3 \mathrm{~m}\). The airplane is flying at standard sea level with a velocity of \(200 \mathrm{~m} / \mathrm{s}\). If the flow is considered to be completely laminar, calculate the boundary layer thickness at the trailing edge and the total skin friction drag. Assume that the wing is approximated by a flat plate. Assume incompressible flow.

Consider an airplane flying with a velocity of \(60 \mathrm{~m} / \mathrm{s}\) at a standard altitude of \(3 \mathrm{~km}\). At a point on the wing, the airflow velocity is \(70 \mathrm{~m} / \mathrm{s}\). Calculate the pressure at this point. Assume incompressible flow.

A high-speed subsonic Boeing 777 airliner is flying at a pressure altitude of \(12 \mathrm{~km}\). A Pitot tube on the vertical tail measures a pressure of \(2.96 \times 10^{4} \mathrm{~N} / \mathrm{m}^{2}\). At what Mach number is the airplane flying?

Consider a Mach 2 airstream at standard sea-level conditions. Calculate the total pressure of this flow. Compare this result with \((a)\) the stagnation pressure that would exist at the nose of a blunt body in the flow and \((b)\) the erroneous result given by Bernoulli's equation, which of course does not apply here.

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