Seventh
International Aerospace Congress IAC'12
Dedicated to the
55th Anniversary of the launch of the First Artificial Satellite of the Earth
Section 3. AERODYNAMICS AND
THERMAL PROCESSES
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INTERACTION OFs AN OBLIQUE SHOCK WAVE WITH THE BOW
SHOCK OF A PLANE CYLINDER IN A HYPERSONIC GAS-PARTICLE FLOW |
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AERODYNAMIC DESIGN FEATURES
OF HIGH-PRESSURE FAN |
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CONTROL supersonic boundary airflow using the
sliding discharge |
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NUMERICAL STUDY OF THE FLOW AROUND SPACE VEHICLES AT
HIGH ALTITUDES |
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CATALYTIC MECHANISMS OF ATOMIC OXYGEN RECOMBINATION
ON THERMAL PROTECTION COATINGS |
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RESEARCH OF THE AERODYNAMIC CHARACTERISTICS OF AN
AIR SCREWS LOCATED IN VICINITY OF THE SCREEN AND AN AIRSHIP BODY |
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Conical Flows Near V-shaped Wings With Attached
Shock Waves On Leading Edges |
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AERODYNAMIC CHARACTERISTICS OF THE MODELS EFFECT OF
THE APPARATUS «PHOBOS-SOIL» |
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THE ANALYSIS OF INFLUENCE OF PURITY OF THE
LIQUID-METAL ENVIRONMENT ON QUALITY THERMAL METALGRAMS AT THE CALORIMETRIC
TESTS OF COOLED DETAILS IN GAS-TURBINE ENGINES AND GAS-TURBINE INSTALLATIONS |
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HYDRODYNAMICS AND HEAT TRANSFER PROBLEMS OF SPACE
LIQUID-DROPLET RADIATORS |
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ON METHOD OF PSEUDOCHARACTERISTICS FOR SOLVING 3D
STATIONARY SUPERSONIC FLOWS OF IDEAL GAS |
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EXPERIMENTAL STUDY AND MODELING THE KINETICS OF
OXYGEN DISSOCIATION BEHIND A SHOCK WAVE AT TEMPERATURES UP TO 11000K |
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SEPARATION OF TURBULENT BOUNDARY LAYER IN SUPERSONIC
CONICAL GAS FLOWS |
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INTERPRETATION OF OBSERVATIONS OF operating Fireball
NETWORKS
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SIMULATION OF THE FLOW IN THE TEST SECTION OF LOW
VELOCITY WIND TUNNEL FOR TWO-DIMENSIONAL APPROACH |
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METHODOLOGY OF THERMAL TESTS OF DETAILS OF AVIATION ENGINES
AND POWER INSTALLATIONS IN THE FUSED METAL WITH HIGH HEAT CONDUCTIVITY |
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ON FORMATION OF AERODYNAMIC CONFIGURATION OF HYPERSONIC
FLIGHT VEHICLE |
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THE METHODOLOGY OF THE ESTIMATION OF
THE QUALITY OF THE THERMOSTATIC ENVIRONMENT AND TERM OF ITS REPLACEMENT AT
THE CALORIMETRIC TESTS |
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THE METHODOLOGY OF THE DESIGNING OF THE CALORIMETRIC
TESTS: DEFINITION OF THE SIZES OF THE BATH IN THE THERMOSTAT AND DEFINITION
OF THE BEGINNING OF THE BLOWING OF THE DETAIL BY COOLING AIR |
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THE ANALYSIS OF RESOLUTION OF THE CALORIMETRIC TESTS
OF COOLED DETAILS IN GAS-TURBINE ENGINES AND GAS-TURBINE INSTALLATIONS |
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THE ANALYSIS OF PROPERTIES OF THE WORKING
ENVIRONMENT OF THE LIQUID-METAL THERMOSTAT AT THE CALORIMETRIC TESTS OF
COOLED DETAILS IN GAS-TURBINE ENGINES AND GAS-TURBINE INSTALLATIONS |
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THE METHODOLOGY of definition of optimum time of THE
BLOWING of THE detail BY cooling air AT THE CALORIMETRIC TESTS |
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BLOWING AND ROUGHNESS EFFECTS IN THE TURBULENT
BOUNDARY LAYER |
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NUMERICAL MODELING OF A FLOW OF AN AIRSHIP NEAR TO THE SCREEN IN VIEW OF AN AIRSCREW JET INFLUENCE Le Quoc Dinh, Dang Ngoc Thanh The
Moscow aviation institute (National research university) "MAI |
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Lepeshkin A.R.
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Abstracts should reach the Organizing
Committee by May 15, 2012.
NEW Extended: June 1, 2012
Correspondence
Professor Mark Liberzon
IAC’12
Petrovka Str., 30/7, Bld. 1, off. 7, Moscow, 127006,
Russia
Tel.: +7 (495) 694-2727
Fax: +7 (495) 650-6010
E-mail: elena@fund.ru
www.fund.ru