#lift force

Bernoulli's Theorem and Applications

An aircraft (m\=4.0×105kg, wing area 600m2) flies level. What is the pressure difference across the wings? (Take g\=9.8m

ΔP⋅A = mg. mg = 4.0×105×9.8 = 3.92×106N, A = 600m2. ΔP = 3.92×106600 = 6533.33Pa≈6533Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 6533 Pa. This satisfies dimensional consistency and physical conditions given, so option C is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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Equation of Continuity and Flow Rate

An aircraft (m\=2.0×105kg, wing area 400m2) flies level. What is the pressure difference across the wings? (Take g\=9.8m

ΔP⋅A = mg. mg = 2.0×105×9.8 = 1.96×106N, A = 400m2. ΔP = 1.96×106400 = 4900Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 4900 Pa. This satisfies dimensional consistency and physical conditions given, so option C is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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Viscosity, Stokes' Law and Reynolds Number

An aircraft (m\=2.5×105kg, wing area 400m2) flies at 900km/h. What is the pressure difference across the wings? (Take g\

ΔP⋅A = mg, mg = 2.5×105×10 = 2.5×106N. A = 400m2. ΔP = 2.5×106400 = 6250Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 6250 Pa. This satisfies dimensional consistency and physical conditions given, so option B is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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Viscosity, Stokes' Law and Reynolds Number

An aircraft (m\=3.5×105kg, wing area 550m2) flies level. What is the pressure difference across the wings? (Take g\=10m/

ΔP⋅A = mg. mg = 3.5×105×10 = 3.5×106N, A = 550m2. ΔP = 3.5×106550 = 6363.64Pa≈6364Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 6364 Pa. This satisfies dimensional consistency and physical conditions given, so option C is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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Equation of Continuity and Flow Rate

An aircraft (m\=3.0×105kg, wing area 450m2) flies level. What is the pressure difference across the wings? (Take g\=10m/

ΔP⋅A = mg. mg = 3.0×105×10 = 3.0×106N, A = 450m2. ΔP = 3.0×106450 = 6666.67Pa≈6667Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 6667 Pa. This satisfies dimensional consistency and physical conditions given, so option C is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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Fluid Pressure, Pascal's Law and Manometers

An aircraft (m\=2.5×105kg, wing area 500m2) flies level. What is the pressure difference across the wings? (Take g\=9.8m

ΔP⋅A = mg. mg = 2.5×105×9.8 = 2.45×106N, A = 500m2. ΔP = 2.45×106500 = 4900Pa. As per NCERT, applying relevant law/formula with correct units and sign convention leads to 4900 Pa. This satisfies dimensional consistency and physical conditions given, so option C is scientifically correct.

Ref: NCBI Bookshelf, Ideal Gas Law: P1V1/T1 = P2V2/T2.

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