FIELD: physics.
SUBSTANCE: invention can be used to determine flow rate of air through an air inlet during flight tests of the propulsive jet engine of hypersonic aircraft. The method includes determining flow rate of air through an air inlet during flight, taking into account distribution of air pressure and temperature on the width L and height H of the input of the air inlet, for which on-board devices for measuring air pressure and temperature - pressure inlets are moved from special grooves, and thermoanemometers are placed together on the surface on the width of the inlet in a finite number of measurement points equidistant from each other. During tests, pressure inlets are moved upwards on the height of the inlet. Static air pressure is measured on the top surface of the pressure inlet and full air pressure is measured on the front face of the pressure inlet. Simultaneously, temperature of the outer surface of the thermoanemometers and ohmic resistance of tungsten filaments lying on the outer surface of the thermoanemometers, heated by electric current, are measured. Said data are then used to successively determine the Mach number of the air stream, temperature of the first and second filaments, convection heat currents on the outer surface of the filaments, static air temperature and air flow rate through the air inlet.
EFFECT: high accuracy of determining air flow rate through an air inlet during flight tests of an on-board the propulsive jet engine and minimising perturbation caused by on-board measuring devices in the air stream entering the air inlet.
7 dwg
