17. The airflow behind a normal shock wave will:a.always be subsonic and in the same direction as the original airflow.b.always be supersonic and in the same direction as the original airflow.C.d.always be subsonic and will be deflected from the direction of the originalairflow.18. As airflow passes through a normal shock wave, which of the following changes instatic pressure (i), density (ii), and Mach number (ii) will occur?(iii)< 1.0< 1.0> 1.0 or < 1.0< 1.0(i)decrease(ii)increa sea.b.increasedecrea seincreasedecrea seC.d.increaseincrea se19.An aerofoil travelling at supersonic speed will:a.have its centre of pressure at 50 % chord.have its centre of pressure at 25% chord.give a larger proportion of lift from the lower surface than from theupper surface, and have its centre of pressure at 50 % chord.give approximately equal lift from the upper and lower surfaces, andhave its aerodynamic centre at 50% chord.b.C.d.P.

The turbulent wake created by the airflow behind the shock wave increases drag. A shock wave forms…

Tow benind a normal shock wave Wl always be subsonic and in the same direction as the origin always be supersonic and in the same direction as the oris may be subsonic or supersonic. always be subsonic and will be deflected from the directi airflow.

Tow benind a normal shock wave Wl always be subsonic and in the same direction as the origin always be supersonic and in the same direction as the oris may be subsonic or supersonic. always be subsonic and will be deflected from the directi airflow.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

17. The airflow behind a normal shock wave will:
a.
always be subsonic and in the same direction as the original airflow.
b.
always be supersonic and in the same direction as the original airflow.
C.
d.
always be subsonic and will be deflected from the direction of the original
airflow.
18. As airflow passes through a normal shock wave, which of the following changes in
static pressure (i), density (ii), and Mach number (ii) will occur?
(iii)
< 1.0
< 1.0
> 1.0 or < 1.0
< 1.0
(i)
decrease
(ii)
increa se
a.
b.
increase
decrea se
increase
decrea se
C.
d.
increase
increa se
19.
An aerofoil travelling at supersonic speed will:
a.
have its centre of pressure at 50 % chord.
have its centre of pressure at 25% chord.
give a larger proportion of lift from the lower surface than from the
upper surface, and have its centre of pressure at 50 % chord.
give approximately equal lift from the upper and lower surfaces, and
have its aerodynamic centre at 50% chord.
b.
C.
d.
P.

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