RESULTS OF THE RESEARCH OF STATIC PRESSURE DISTRIBUTION ON THE HEAD PART MISSILE M-100 AERO PHYSICAL SYSTEMS ON THE BASIS OF THE NUMERICAL METHOD OF CALCULATION AND FLIGHT EXPERIMENT FOR MACH NUMBERS 1,4 М4,2, REYNOLDS ReL, ≤108 , ACCELERATION a ≤32g IN THE CONDITIONS OF AERODYNAMIC HEATING

RESULTS OF THE RESEARCH OF STATIC PRESSURE DISTRIBUTION ON THE HEAD PART MISSILE M-100 AERO PHYSICAL SYSTEMS ON THE BASIS OF THE NUMERICAL METHOD OF CALCULATION AND FLIGHT EXPERIMENT FOR MACH NUMBERS 1,4 М4,2, REYNOLDS ReL, ≤108 , ACCELERATION a ≤32g IN THE CONDITIONS OF AERODYNAMIC HEATING

Article is devoted to end-to-end solution of a problem of reliability and reliability of data on distribution of static pressure to surfaces of a head part of a missile M-100 aerophysical system in the range of Reynolds numbers of a flow , Mach numbers , an acceleration  in flight conditions on a...

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Bibliographic Details
Main Authors: Анатолий Михайлович Павлюченко, Александр Николаевич Шийко, Андрей Викторович Скорик
Format: Article
Language:English
Published: National Aerospace University «Kharkiv Aviation Institute» 2017-08-01
Series:Авіаційно-космічна техніка та технологія
Subjects:
статичний тиск на головній частині
льотний експеримент
пряме вимірювання тиску
рівняння навье-стокса
моделі турбулентності
програмний продукт ansys cfx
порівняння розрахункових і льотних даних по тиску
Online Access:http://nti.khai.edu/ojs/index.php/aktt/article/view/495

Internet

http://nti.khai.edu/ojs/index.php/aktt/article/view/495

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