To determine the airspeed of the aircraft, we can use the Bernoulli equation for incompressible flow, which relates the pressure difference to the dynamic pressure. The dynamic pressure can be used to find the airspeed.

1. **Identify the given values:**
- Altitude: 8,000 m
- Air density (ρ): 0.55 kg/m³
- Static pressure (P_static): 600 hPa = 60000 Pa (since 1 hPa = 100 Pa)
- Total pressure (P_total): 620 hPa = 62000 Pa

2. **Calculate the dynamic pressure (q):**
The dynamic pressure is the difference between the total pressure and the static pressure.
$$
q = P_{total} - P_{static}
$$
$$
q = 62000 \, \text{Pa} - 60000 \, \text{Pa} = 2000 \, \text{Pa}
$$

3. **Use the dynamic pressure to find the airspeed (V):**
The dynamic pressure is also given by the equation:
$$
q = \frac{1}{2} \rho V^2
$$
Solving for V:
$$
V = \sqrt{\frac{2q}{\rho}}
$$
Substituting the known values:
$$
V = \sqrt{\frac{2 \times 2000 \, \text{Pa}}{0.55 \, \text{kg/m}^3}}
$$
$$
V = \sqrt{\frac{4000}{0.55}}
$$
$$
V = \sqrt{7272.73}
$$
$$
V \approx 85.28 \, \text{m/s}
$$

4. **Check the options:**
The calculated airspeed (85.28 m/s) does not match any of the given options (200 m/s, 250 m/s, 300 m/s, 350 m/s). Therefore, there might be an error in the problem statement or the given options.

Given the discrepancy, it is important to recheck the problem statement and the calculations. However, based on the provided data and standard Bernoulli equation, the calculated airspeed is approximately 85.28 m/s.

Question

To determine the airspeed of the aircraft, we can use the Bernoulli equation for incompressible flow, which relates the pressure difference to the dynamic pressure. The dynamic pressure can be used to find the airspeed.

1. **Identify the given values:**
   - Altitude: 8,000 m
   - Air density (ρ): 0.55 kg/m³
   - Static pressure (P_static): 600 hPa = 60000 Pa (since 1 hPa = 100 Pa)
   - Total pressure (P_total): 620 hPa = 62000 Pa

2. **Calculate the dynamic pressure (q):**
   The dynamic pressure is the difference between the total pressure and the static pressure.
   $$
   q = P_{total} - P_{static}
   $$
   $$
   q = 62000 \, \text{Pa} - 60000 \, \text{Pa} = 2000 \, \text{Pa}
   $$

3. **Use the dynamic pressure to find the airspeed (V):**
   The dynamic pressure is also given by the equation:
   $$
   q = \frac{1}{2} \rho V^2
   $$
   Solving for V:
   $$
   V = \sqrt{\frac{2q}{\rho}}
   $$
   Substituting the known values:
   $$
   V = \sqrt{\frac{2 \times 2000 \, \text{Pa}}{0.55 \, \text{kg/m}^3}}
   $$
   $$
   V = \sqrt{\frac{4000}{0.55}}
   $$
   $$
   V = \sqrt{7272.73}
   $$
   $$
   V \approx 85.28 \, \text{m/s}
   $$

4. **Check the options:**
   The calculated airspeed (85.28 m/s) does not match any of the given options (200 m/s, 250 m/s, 300 m/s, 350 m/s). Therefore, there might be an error in the problem statement or the given options.

Given the discrepancy, it is important to recheck the problem statement and the calculations. However, based on the provided data and standard Bernoulli equation, the calculated airspeed is approximately 85.28 m/s.

Knowee AI · Accepted Answer

To determine the airspeed of the aircraft, we can use the Bernoulli equation for incompressible flow, which relates the pressure difference to the dynamic pressure. The dynamic pressure can be used to find the airspeed.

1. **Identify the given values:**
   - Altitude: 8,000 m
   - Air density (ρ): 0.55 kg/m³
   - Static pressure (P_static): 600 hPa = 60000 Pa (since 1 hPa = 100 Pa)
   - Total pressure (P_total): 620 hPa = 62000 Pa

2. **Calculate the dynamic pressure (q):**
   The dynamic pressure is the difference between the total pressure and the static pressure.
   $$
   q = P_{total} - P_{static}
   $$
   $$
   q = 62000 \, \text{Pa} - 60000 \, \text{Pa} = 2000 \, \text{Pa}
   $$

3. **Use the dynamic pressure to find the airspeed (V):**
   The dynamic pressure is also given by the equation:
   $$
   q = \frac{1}{2} \rho V^2
   $$
   Solving for V:
   $$
   V = \sqrt{\frac{2q}{\rho}}
   $$
   Substituting the known values:
   $$
   V = \sqrt{\frac{2 \times 2000 \, \text{Pa}}{0.55 \, \text{kg/m}^3}}
   $$
   $$
   V = \sqrt{\frac{4000}{0.55}}
   $$
   $$
   V = \sqrt{7272.73}
   $$
   $$
   V \approx 85.28 \, \text{m/s}
   $$

4. **Check the options:**
   The calculated airspeed (85.28 m/s) does not match any of the given options (200 m/s, 250 m/s, 300 m/s, 350 m/s). Therefore, there might be an error in the problem statement or the given options.

Given the discrepancy, it is important to recheck the problem statement and the calculations. However, based on the provided data and standard Bernoulli equation, the calculated airspeed is approximately 85.28 m/s.

An aircraft is flying at an altitude of 8,000 m, where the air density is 0.55 kg/m³. The barometer reading at the static port is 600 hPa, and the reading at the Pitot tube is 620 hPa. What is the approximate airspeed of the aircraft?a) 200 m/sb) 250 m/sc) 300 m/sd) 350 m/s

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