1 Mach angle α is given by (a) cos −1 (M ) (c) cos −1 ( 1/M ) (b) sin −1 (1 /M ) (d) sin −1 (M ) 2 The type of nozzle preferred in supersonic aircraft engines is (a) convergent nozzle (c)...

1 Mach angle α is given by

(a) cos
⁻¹
(M ) (c) cos
⁻¹
( 1/M )

(b) sin⁻¹
(1 /M ) (d) sin
⁻¹
(M )

2 The type of nozzle preferred in supersonic aircraft engines is

(a) convergent nozzle (c) convergent–divergent nozzle

(b) divergent nozzle (d) any of these