FIELD: transport.
SUBSTANCE: invention refers to cooling methods of elements of constructions, mainly super- and hypersonic aircrafts. Method involves injection of cooling gas through perforated inserts to the area where head end interacts with the flow slipping the flying machine. At that, cooling gas jets are swirled; for that purpose on walls of perforation holes there made are screw or spiral grooves. Diametre of holes is taken within 0.26-0.66 of thickness of perforated insert, and non-dimensional injection parametre B=pV/(α/Cp) - within 3-8. The above grooves made on walls of holes can be made in the form of standardised metric thread. Therefore, turbulent vortices are suppressed in high-gradient zones of cooling gas flow when it is mixed with slip flow.
EFFECT: increasing thermal protection efficiency by decreasing the required cooling gas consumption.
4 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD FOR THERMAL SHIELDING AIRCRAFT NOSE | 2010 |
|
RU2452669C1 |
| METHOD FOR AIRCRAFT HEAD-END COOLING | 2011 |
|
RU2463209C1 |
| METHOD TO VARY HYPERSONIC AIRCRAFT AERODYNAMIC CHARACTERISTICS AND DEVICE TO THIS END | 2008 |
|
RU2383469C1 |
| METHOD OF CONTROL OVER SUPERSONIC AIRCRAFT OVERFLOW | 2014 |
|
RU2559193C1 |
| METHOD AND DEVICE FOR COOLING FRONT EDGE OF STREAMLINED BODY | 2000 |
|
RU2186223C2 |
| METHOD OF FLOW CONTROL AROUND FLYING VEHICLE | 1990 |
|
RU2173657C2 |
| METHOD OF CHANGE OF AERODYNAMIC CHARACTERISTICS OF FLYING VEHICLE CONTROL SURFACES AND DEVICE FOR REALIZATION OF THIS METHOD | 2004 |
|
RU2272746C1 |
| METHOD AND AIR VEHICLE FOR MOVING IN PLANETARY ATMOSPHERE WITH SPEEDS ABOVE THE FIRST SPACE AND HIGHLY INTEGRATED HYPERSONIC VEHICLE APPARATUS (VERSIONS) FOR IMPLEMENTATION OF THE METHOD | 2012 |
|
RU2618831C2 |
| METHOD OF CHANGE OF AERODYNAMIC CHARACTERISTICS OF SUBSONIC FLYING VEHICLE AND DEVICE FOR REALIZATION OF THIS METHOD | 2004 |
|
RU2282563C2 |
| METHOD OF IGNITION AND COMBUSTION OF FUEL IN ATHODYD | 2013 |
|
RU2550209C1 |
