Transonic flow over wing CO5

The freestream Mach number which gives sonic velocity somewhere on the boundary of an object placed in the fluid stream is called

(a)  

Which of the following design features of an aircraft wing will increase M_crit ?

• swept wing

• thinner wing section

• less t/c

• all the above

An aircraft enters into transonic regime when it reaches the M_crit. Say True or False.

• True

• False

Which of the following statement is incorrect with respect to transonic area rule?

• cross-sectional area of the body should have a

  smooth variation with longitudinal distance along the body

• there should be no

  rapid or discontinuous changes in the cross-sectional area distribution

• the body cross section should be decreased

  in the vicinity of the wing

• none of the above

Although the supercritical airfoil and an equivalent

standard airfoil may have the same critical Mach number, the drag-divergence

Mach number for the supercritical airfoil is much lesser. Say True or False?

• True

• False

Choose the incorrect statements?

(i) Supercritical airfoils are

designed to operate far above the critical Mach number

(ii) Drag divergence Mach number decreases with supercritical airfoils

(iii) Shock strength is reduced as a result of supercritical airfoil

(iv) boundary layer separation is more severe

• (i), (iii)

• (i), (iv)

• (ii), (iii)

• (ii), (iv)

Which aircraft utilizes area rule, F102 or F102A?

(a)  

The flowfield between the shock wave and the body is defined as the

(a)  

Which are the important flow phenomena that occur in hypersonic flow over a body?

• Thin shock layers

• Vorticity interaction

• Aerodynamic heating

• High speed