The paper is focused on the research of the spatial way of flow inhibiting applied to supersonic and hypersonic input devices of aircrafts. To inhibit the flow a structural element, the corner body, is used. It provides spatial compression from the leading edge of the input device while the second (reflected) shock wave is formed in the non-contiguous flow area. The results of an experimental research of two spatial inlets based on the flow in a corner body with the Mach interaction of shock waves are presented.

Topics
Shock waves, Aircraft
1.
Trexler
,
C. A.
, &
Souders
,
S. W.
 (
1975
).
Design and performance at a local Mach number of 6 of an inlet for an integrated Scramjet concept.[wind tunnel models-aircraft design]
.
Google Scholar
 
2.
Gutov
 
B.I.
,
Zatoloka
 
V. V.
 (
1987
).
Convergent currents and air intakes, the simplest and with an extremely compact channel
.
Izv. AN USSR. PMTF
,
2
,
57
–
62
.
Google Scholar
 
3.
Borovikov
 
A.D.
 (
1984
).
Comparison of the design parameters of the spatial intake with three shock waves of the scramjet engine with traditional air intakes
.
Design, construction and strength of structural elements of jet engines.
Sat.-MAI, 13-18.
Google Scholar
 
4.
Gunko
,
Y.P.
, &
Mazhule
,
I.I.
 (
2011
).
Design of supersonic three-dimensional air intakes using a flat isoentropic compression flow
.
Teplofizika i ajeromehanika
,
18
(
1
),
95
–
108
.
Google Scholar
 
5.
Tolmachev
 
V.I.
 (
2018
).
Designing a hypersonic input device based on the flow in an corner body
.
Engineering Journal: Science and Innovation.
No.
5
(
77
). DOI:
https://doi.org/10.18698/2308-6033-2018-5-1760
.
Google Scholar
 
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