FIELD: rocketry and aeronautical engineering. SUBSTANCE: nose fairing is made in form of envelope having shape of cone, paraboloid or combination of them. Its outer surface is provided with helical passages of varying section; they form helical fins of envelope. When such fairing is used on supersonic flying vehicles, density of thermal flux and aerodynamic losses on surface of fairing are reduced. EFFECT: reduced aerodynamic losses on fairing surface. 2 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
METHOD OF CONTROL OF SUPERSONIC AIR FLOW OVER AIRCRAFT | 2004 |
|
RU2268198C1 |
SURFACE OF BODY FOR REDUCTION OF FRICTION AND SURFACE OF BODY FOR INTENSIFICATION OF HEAT EXCHANGE | 2006 |
|
RU2425260C2 |
METHOD OF CONTROL OF FLOW AROUND FLYING VEHICLE | 2004 |
|
RU2283794C2 |
AIRCRAFT | 2012 |
|
RU2521164C1 |
CONTROL METHOD OF FLOW OF UNPILOTED AIRCRAFT | 2010 |
|
RU2415373C1 |
SUPERSONIC AIRCRAFT | 2013 |
|
RU2548200C2 |
AIRCRAFT | 2012 |
|
RU2517629C1 |
METHOD FOR THERMAL CONTROL DURING HEAT TESTS OF ANTENNA DOMES OF MISSILES | 2017 |
|
RU2676385C1 |
AIRCRAFT | 2012 |
|
RU2517627C1 |
ROCKET LAUNCHED FROM LAUNCHING TUBE | 1999 |
|
RU2148778C1 |
Authors
Dates
1998-08-27—Published
1997-08-27—Filed