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Air is streaming over both the aeroplane wings such that its speed is 85 m-s-1 over the upper surface and 75 m-s-1 at the lower surface. If the wings are 10 m long and have an average width of 2 m, then lift of the wind on aeroplane is (Take density of air = 1.5 kg-m-3)
- a)12 kN
- b)24 kN
- c)48 kN
- d)72 kN
Correct answer is option 'C'. Can you explain this answer?
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Air is streaming over both the aeroplane wings such that its speed is ...
Understanding Lift in Aerodynamics
To calculate the lift generated by an airplane wing, we can use Bernoulli's principle, which states that an increase in the speed of a fluid occurs simultaneously with a decrease in pressure.
Step 1: Calculate the Pressure Difference
The pressure difference between the upper and lower surfaces of the wing can be calculated using Bernoulli's equation:
- \( P_1 + \frac{1}{2} \rho v_1^2 = P_2 + \frac{1}{2} \rho v_2^2 \)
Where:
- \( P_1 \) = Pressure on the upper surface
- \( P_2 \) = Pressure on the lower surface
- \( \rho \) = Density of air = 1.5 kg/m³
- \( v_1 \) = Speed over the upper surface = 85 m/s
- \( v_2 \) = Speed over the lower surface = 75 m/s
Rearranging gives us the pressure difference:
- \( \Delta P = P_2 - P_1 = \frac{1}{2} \rho (v_1^2 - v_2^2) \)
Substituting the values:
- \( \Delta P = \frac{1}{2} \times 1.5 \times (85^2 - 75^2) \)
Calculating:
- \( v_1^2 = 7225 \)
- \( v_2^2 = 5625 \)
- \( \Delta P = \frac{1}{2} \times 1.5 \times (7225 - 5625) = \frac{1}{2} \times 1.5 \times 1600 = 1200 \) Pa
Step 2: Calculate the Lift Force
The lift force can be calculated using the formula:
- \( L = \Delta P \times A \)
Where \( A \) is the wing area:
- \( A = \text{length} \times \text{width} = 10 \, m \times 2 \, m = 20 \, m² \)
Thus, the lift is:
- \( L = 1200 \, Pa \times 20 \, m² = 24000 \, N = 24 \, kN \)
Since the question states the correct answer is C (48 kN), ensure the interpretation of the problem aligns with the provided values or check for additional factors influencing the lift calculation (e.g., angle of attack, wing shape). The apparent discrepancy could arise from assumptions in the initial conditions or simplifications in the calculations.
To calculate the lift generated by an airplane wing, we can use Bernoulli's principle, which states that an increase in the speed of a fluid occurs simultaneously with a decrease in pressure.
Step 1: Calculate the Pressure Difference
The pressure difference between the upper and lower surfaces of the wing can be calculated using Bernoulli's equation:
- \( P_1 + \frac{1}{2} \rho v_1^2 = P_2 + \frac{1}{2} \rho v_2^2 \)
Where:
- \( P_1 \) = Pressure on the upper surface
- \( P_2 \) = Pressure on the lower surface
- \( \rho \) = Density of air = 1.5 kg/m³
- \( v_1 \) = Speed over the upper surface = 85 m/s
- \( v_2 \) = Speed over the lower surface = 75 m/s
Rearranging gives us the pressure difference:
- \( \Delta P = P_2 - P_1 = \frac{1}{2} \rho (v_1^2 - v_2^2) \)
Substituting the values:
- \( \Delta P = \frac{1}{2} \times 1.5 \times (85^2 - 75^2) \)
Calculating:
- \( v_1^2 = 7225 \)
- \( v_2^2 = 5625 \)
- \( \Delta P = \frac{1}{2} \times 1.5 \times (7225 - 5625) = \frac{1}{2} \times 1.5 \times 1600 = 1200 \) Pa
Step 2: Calculate the Lift Force
The lift force can be calculated using the formula:
- \( L = \Delta P \times A \)
Where \( A \) is the wing area:
- \( A = \text{length} \times \text{width} = 10 \, m \times 2 \, m = 20 \, m² \)
Thus, the lift is:
- \( L = 1200 \, Pa \times 20 \, m² = 24000 \, N = 24 \, kN \)
Since the question states the correct answer is C (48 kN), ensure the interpretation of the problem aligns with the provided values or check for additional factors influencing the lift calculation (e.g., angle of attack, wing shape). The apparent discrepancy could arise from assumptions in the initial conditions or simplifications in the calculations.
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Air is streaming over both the aeroplane wings such that its speed is 85 m-s-1 over the upper surface and 75 m-s-1at the lower surface. If the wings are 10 m long and have an average width of 2 m, then lift of the wind on aeroplane is (Take density of air = 1.5 kg-m-3)a)12 kNb)24 kNc)48 kNd)72 kNCorrect answer is option 'C'. Can you explain this answer?
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Air is streaming over both the aeroplane wings such that its speed is 85 m-s-1 over the upper surface and 75 m-s-1at the lower surface. If the wings are 10 m long and have an average width of 2 m, then lift of the wind on aeroplane is (Take density of air = 1.5 kg-m-3)a)12 kNb)24 kNc)48 kNd)72 kNCorrect answer is option 'C'. Can you explain this answer? for NEET 2024 is part of NEET preparation. The Question and answers have been prepared according to the NEET exam syllabus. Information about Air is streaming over both the aeroplane wings such that its speed is 85 m-s-1 over the upper surface and 75 m-s-1at the lower surface. If the wings are 10 m long and have an average width of 2 m, then lift of the wind on aeroplane is (Take density of air = 1.5 kg-m-3)a)12 kNb)24 kNc)48 kNd)72 kNCorrect answer is option 'C'. Can you explain this answer? covers all topics & solutions for NEET 2024 Exam. Find important definitions, questions, meanings, examples, exercises and tests below for Air is streaming over both the aeroplane wings such that its speed is 85 m-s-1 over the upper surface and 75 m-s-1at the lower surface. If the wings are 10 m long and have an average width of 2 m, then lift of the wind on aeroplane is (Take density of air = 1.5 kg-m-3)a)12 kNb)24 kNc)48 kNd)72 kNCorrect answer is option 'C'. Can you explain this answer?.
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