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If the magnitude of the pressure fluctuations generated by a source triple from \(6 \mathrm{~Pa}\) to \(18 \mathrm{~Pa}\), what is the change in decibel level?

Short Answer

Expert verified
The change in decibel level is approximately 9.54 dB.

Step by step solution

01

Understand the Problem

We are given a change in pressure magnitude from \(6 \, \text{Pa}\) to \(18 \, \text{Pa}\) and need to determine the change in decibel level. We will use the formula for sound pressure level in decibels.
02

Inventory the Formula

The formula for sound pressure level (SPL) in decibels is \( L = 20 \log_{10} \left( \frac{p}{p_0} \right) \), where \( p \) is the sound pressure and \( p_0 \) is the reference sound pressure level, typically \( 20 \, \mu\text{Pa} \). However, since we are comparing relative changes, \( p_0 \) will cancel out.
03

Calculate Initial Sound Level

Calculate the initial sound level for \(6 \, \text{Pa}\):\[ L_1 = 20 \log_{10} \left( \frac{6}{20 \times 10^{-6}} \right) \]This simplifies to: \[ L_1 = 20 \log_{10} (300,000) \]
04

Calculate Final Sound Level

Calculate the final sound level for \(18 \, \text{Pa}\):\[ L_2 = 20 \log_{10} \left( \frac{18}{20 \times 10^{-6}} \right) \]This simplifies to: \[ L_2 = 20 \log_{10} (900,000) \]
05

Find the Change in Decibels

The change in decibel level is the difference between the final and initial sound levels: \[ \Delta L = L_2 - L_1 = 20 \log_{10} \left( \frac{900,000}{300,000} \right) \]This simplifies to: \[ \Delta L = 20 \log_{10} (3) \]Calculate \( \log_{10} (3) \approx 0.4771 \), so the change is approximately \[ \Delta L = 20 \times 0.4771 = 9.54 \, \text{dB} \].

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Key Concepts

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

Decibel Scale
The decibel scale is used to measure the intensity of sound. It is a logarithmic scale, which means it doesn't increase linearly like a ruler. Instead, each unit increase on this scale represents a tenfold increase in intensity. This is because the human ear perceives sound intensity logarithmically. The scale is named after Alexander Graham Bell, and is abbreviated as dB.

In practical terms, using the decibel scale allows us to express very large or very small quantities of sound intensity in a manageable way. For example, normal conversation is typically around 60 dB, while a whisper is about 30 dB, and a rock concert around 120 dB. The range is wide and accommodates the diverse ways we experience sound.
Logarithmic Function
Logarithmic functions are essential in understanding the decibel scale. A logarithm answers the question: "To what power must we raise a specific base (commonly 10) to get a certain number?" This function is expressed as \( y = \log_{b}(x) \), where \( b \) is the base and \( x \) is the number for which we are seeking the exponent.

In the context of sound, when calculating sound pressure level, we often use the formula: \( L = 20 \log_{10}(\frac{p}{p_0}) \). Here, \( p \) represents the measured sound pressure, and \( p_0 \) is the reference pressure. Logarithmic functions help compare changes in sound pressure to changes in human perception, capturing the vast range of sound levels into a simple scale.
Pressure Fluctuations
Pressure fluctuations in the air are what we interpret as sound. Sound is produced when a source causes pressure differences in the air particles, generating waves that travel to our ears. These pressure fluctuations can vary widely in strength.

In our example problem, the pressure fluctuation increased from \( 6 \text{ Pa} \) to \( 18 \text{ Pa} \). To understand how this affects the perceived sound, we must convert these pressure changes into decibels. The tripling of pressure causes a specific increase in the sound level, as perceived by the listener, calculated using a logarithmic function.
Reference Sound Pressure
The reference sound pressure \( (p_0) \) is fundamental when calculating sound pressures in decibels. It acts as a baseline for all measurements. Standardly, for air, this reference is \( 20 \mu\text{Pa} \), which is approximately the quietest sound that the average human ear can detect.

By using a reference sound pressure, we create a consistent standard for measuring and comparing sounds. This allows different pressure levels to be expressed and contextualized on the decibel scale. Whether calculating the energy from a whisper or a jet engine, the reference sound pressure remains constant, enabling meaningful comparisons. Without it, assessing the significance of changes in sound pressure would be tricky.

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Most popular questions from this chapter

Air flows through an insulated pipe section that is \(0.50 \mathrm{~m}\) long and has a diameter of \(50 \mathrm{~mm}\). At the entrance to the pipe, the Mach number is \(0.6,\) the pressure is \(150 \mathrm{kPa}\), and the temperature is \(27^{\circ} \mathrm{C}\). If the average friction factor in the pipe is \(0.020,\) determine the Mach number, temperature, and pressure at the exit of the pipe section.

A mega bomb blast generates a normal shock wave that propagates at a speed of \(650 \mathrm{~m} / \mathrm{s}\) into stagnant air at a temperature and pressure of \(15^{\circ} \mathrm{C}\) and \(90 \mathrm{kPa}\), respectively. Calculate the changes in temperature, pressure, and velocity that are generated in the air by the shock wave.

At the entrance to a 50 -m-long, 75 -mm-diameter insulated duct, the stagnation pressure of the airflow is \(200 \mathrm{kPa}\) and the stagnation temperature is \(150^{\circ} \mathrm{C}\). Under unchoked conditions, the velocity at the entrance is \(120 \mathrm{~m} / \mathrm{s}\). The average friction factor is estimated as \(0.020 .\) Determine the mass flow rate through the duct and state whether the flow is choked.

A CD nozzle with a throat diameter of \(40 \mathrm{~mm}\) connects air in a source reservoir to a discharge reservoir, where the diameter of the nozzle exit is \(90 \mathrm{~mm}\). When the pressure and temperature in the source reservoir are \(101 \mathrm{kPa}\) and \(15^{\circ} \mathrm{C}\), respectively, a normal shock occurs at the nozzle exit. Determine the back pressure on the nozzle and the mass flow rate through the nozzle under this condition.

A supersonic aircraft flies at a Mach speed of 1.8 in an environment where the temperature is \(-40^{\circ} \mathrm{C}\) and the pressure is \(30 \mathrm{kPa}\). Under this condition, a normal shock is formed in front of the nose of the aircraft. Estimate the temperature and pressure at the stagnation point on the nose of the aircraft. What is the change in entropy across the normal shock?

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