Gaseous flow over an airfoil is always compressible because of very high compressibility value of gases.

Always true

Always false

True for low speeds

True only for high speeds

Correct Answer : True only for high speeds

Explanation : Gases have high compressibility values which states that for a given pressure change, the density change can be higher giving a compressible flow. But low speed flows are an exception since the pressure change across the field is small. This dominates the high compressibility value giving an incompressible flow.

Recently Updated in Aerodynamics Questions

The total enthalpy in a general flow at point 1 is H1 and at point 2, which is downstream, is H2. Then __________

H1>H2 always

H2>H1 always

H1=H2 for general flow

H1=H2 for adiabatic flow

Correct Answer : Option (D) : H1=H2 for adiabatic flow

Explaination : The total enthalpy at two points along the flow may or may not be equal in general. The total enthalpies are equal in case of an adiabatic flow between the two points in consideration.

For a steady, inviscid, adiabatic flow of a gas, the total temperate is constant along the flow.

True always

False always

False only for calorically perfect gas

True only for calorically perfect gas

Correct Answer : Option (D) : True only for calorically perfect gas

Explanation : The total enthalpy of a steady, inviscid, adiabatic gaseous flow is constant. For a calorically perfect gas the total enthalpy can be written in terms of total temperature times the specific heat at constant pressure (which is also a constant). Thus, the total temperature is also a constant.

Select the incorrect statement if all the streamlines of the steady, inviscid, adiabatic flow originate from a common uniform freestream.

h0 is not equal to the freestream value

h0 is constant along the entire flow

h + V² = h0 is energy equation per unit mass

Stagnation enthalpy is same for each streamline

Correct Answer : Option (A) : h0 is not equal to the freestream value

Explaination : h0 is the stagnation enthalpy for the steady, inviscid, adiabatic flow which is equal to the static enthalpy plus kinetic energy, all per unit mass. If all the streamlines originate from a common freestream, stagnation enthalpy is equal to the freestream value and is constant along the flow i.e. same for all streamlines.