Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

2014 ◽  
Author(s):  
Johannes Riehmer ◽  
Edder Rabadan ◽  
Ali Guelhan ◽  
Bernhard Weigand
Keyword(s):  
Wind Tunnel ◽  
Blow Down ◽  
Numerical Investigations ◽  
Flight Condition

Design of a continuous portable indraft supersonic wind tunnel

2020 ◽  
pp. 030641902090734
Author(s):  
Monty Bruckman II ◽  
Lance W Traub
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Sound Level ◽  
Wind Tunnels ◽  
Supersonic Wind Tunnel ◽  
Blow Down ◽  
Hands On ◽  
Compressible Fluid Flow ◽  
Aeronautical Engineering ◽  
Design And Manufacture

Programs in mechanical and aeronautical engineering commonly include courses in compressible fluid flow. As such, learning can be greatly enhanced if theory is taught in conjunction with hands on experimentation. While supersonic wind tunnels are not uncommon at many universities, such facilities are generally of the blow down configuration. Consequently, run time is very short and ear protection is required during operation, potentially hindering instruction. Furthermore, blow down configurations are typically expensive and large. This article presents the design and manufacture of a continuous, indraft, miniature supersonic wind tunnel. The tunnel was designed for a nominal test section Mach number of 2; validation indicated a Mach number of 1.96 was achieved. Vacuum was provided by a regenerative blower. The facility is portable and quiet; measurements indicated that the sound level around the tunnel when operational was less than 81 dB (compared to 119dB generated by the department’s blow down supersonic wind tunnel).

Generation of Intake Distortion due to Angle of Attack for a High Bypass Turbofan Model

2014 ◽  
Author(s):  
Jan-Hendrik Krone ◽  
Jens Friedrichs
Keyword(s):  
Wind Tunnel ◽  
Angle Of Attack ◽  
Experimental Setup ◽  
Jet Engine ◽  
Numerical Investigations ◽  
Fan Performance ◽  
Aerodynamic Interaction ◽  
Inlet Conditions ◽  
The University ◽  
Operating Points

This article presents a new fan testing concept which was developed by the University of Braunschweig. The aim of the concept is to provide an experimental setup for integrated jet engine fan investigations. This integrated setup includes a full bypass model with nacelle geometry in order to obtain all aerodynamic interaction effects. Since these interactions have a strong dependency from fan inlet conditions the facility provides wind tunnel capacities. Generating both uniform and angle of attack inlet conditions it is possible to investigate fan performance during the most critical operating points of a civil flight mission. The main innovation of the wind tunnel is the crosswind concept for generating angle of attack conditions in case of a non-pitchable fan unit. Numerical investigations in this paper are intended to validate this new concept by means of typical angle of attack simulations. The results show that the crosswind concept is able to generate equivalent cp-characteristics as obtained for the reference simulations at the nacelle 6 o‘clock and 12 o‘clock positions.

Development of the Reattached Flow Behind Surface-Mounted Two-Dimensional Prisms

1988 ◽  
Vol 110 (2) ◽  
pp. 127-133 ◽  
Author(s):  
J. Antoniou ◽  
G. Bergeles
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Open Circuit ◽  
Two Dimensional ◽  
Blow Down ◽  
Length Scales ◽  
Turbulent Eddies ◽  
Flow Parameters ◽  
Varying Length ◽  
Dimensional Surface

Velocity and turbulence measurements are presented for the region after reattachment behind a two dimensional surface-mounted prism of varying length. The prism is mounted on the floor of an open circuit blow down wind tunnel and flow parameters for the developing boundary layer are deduced from the measurements; longitudinal integral time and length scales are estimated through autocorrelations. Reattchment on top of the prism, due to its increased length, affects the characteristics of the developing boundary layer; in this case the shear layer originating from the up-stream edge of the prism splits twice at reattachment points on top and behind the prism and the integral length scales of the turbulent eddies are found to be smaller due to the splitting.

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