The invention discloses a transient
impact type high-speed wind tunnel low supersonic velocity flow field testing method and spray
pipe devices thereof, which belong to the technical field of wind tunnel tests. In the prior art, an ideal low supersonic velocity flow field cannot be realized, and
test requirements cannot be met. The transient
impact type high-speed wind tunnel low supersonic velocity flow field testing method utilizes the newly designed M1.3, M1.35 and M1.4 spray
pipe devices combined with an aperture wall test section to establish a low supersonic velocity flow field in a transient
impact wind tunnel, and adopts a Mach number control method to obtain ideal flow field
control quality; through the analysis of the axial Mach number distribution of the test section at different expansion angles, the method determines that the smaller the expansion angle of the test section at low
supersonic speed, the better the uniformity of the flow field, and the expansion angle of 0 degree is selected as a tunnel
body condition; the
nozzle devices are combined with the aperture wall test section, and a test section expansion angle and flow field
control mode is used to obtain a qualified flow field that meets the requirements of the national military standard; the ideal low supersonic velocity flow field and the
test requirements are achieved; and a hardware basis is provided for realizing the ideal low supersonic velocity flow field and meeting
test requirements by adopting spray
pipe aerodynamic profiles of the M1.3, M1.35 and M1.4.