Home           Products           Company           Contact us     
> Fundamentals of Fluid Mechanics
> Steady Incompressible Flow
> Flow around Bodies
> Steady Flow of Compressible Fluids
> Examples of Transient Flow
> Hydraulic Fluid Energy Machines
> Components in Piping Systems and Plant Design
> Fluidic Experimental Plants
> Hydraulics for Civil Engineering
Products  |  Fluid Mechanics  |  Steady Flow of Compressible Fluids  |  HM 172
HM 172 Supersonic Wind Tunnel with Schlieren Optics Show data sheet (pdf file) Print page
Technical Description

  Subsonic and supersonic flows behave differently. Thus for example, a constriction in cross section of the flow at subsonic speed causes an increase in velocity, and at supersonic speed causes velocity to slow down. Understanding these fundamental phenomena of supersonic flows helps in the design of e.g. gas and steam turbines, jets or rockets.
  HM 172 is an "Eiffel" type open wind tunnel used to study the aerodynamic properties of various drag bodies at subsonic or supersonic flow.
  A fan sucks air from the environment through the supersonic wind tunnel. There is a subsonic nozzle located at the air inlet, in which the intake air accelerates. The carefully designed contour of the subsonic nozzle with integrated flow straightener ensures a uniform velocity distribution with little turbulence in the subsequent measurement section. In the closed measurement section, the air is accelerated further and flows around a drag body (rocket, projectile, double wedge and wedge). Further down the supersonic wind tunnel, the air flow in slowed down in supersonic and subsonic diffusers and comes through a suction filter into the fan. Here, the air is compressed and then emitted back into the environment. A sound damper at the air outlet limits the sound level.
  Interchangeable walls with different contours are used in the measurement section to generate flow velocities up to Mach 1,8.

  The Schlieren optics supplied allow direct observation of the supersonic flow and the resulting shock fronts. Pressures are detected with sensors, transmitted directly to a PC via USB and analysed there using the software supplied. Additionally, the pressure is displayed on a manometer at the measuring point. The continuous method of operation means there is enough time available for observation and taking measurements.
  The well-structured instructional material sets out the fundamentals and provides a step-by-step guide through the experiments.


Learning Objectives / Experiments

- pressure curves in supersonic nozzles (de Laval

- pressure curves and losses in tunnel flows with

  Mach > 1
- observe shock waves in drag bodies using

  Schlieren optics
- determining the Mach number from the angle of the

  shock waves
- comparison of theory and experiment


* Pressure curves and pressure losses at subsonic

  and supersonic flow1
* Interchangeable walls in the measurement section

  for velocities up to Mach 1,81
* Schlieren optics for visualisation of Mach lines and

  shock waves on drag bodies

Alternative products
HM 170 -- Open Wind Tunnel
HM 172 Supersonic Wind Tunnel

[1] investigation of pressure curves in supersonic flow
[2] visualisation of Mach lines and shock waves using Schlieren optics
[3] continuously operating, open supersonic wind tunnel, low pressure principle
[4] positive displacement fan with variable speed
[5] interchangeable walls in the measurement section produce velocities up to Mach 1,8
[6] drag bodies: rocket, projectile, double wedge and wedge
[7] manometer for displaying the pressure in the measurement point
[8] LabVIEW software for data acquisition (pressure measurement) via USB under Windows XP or Windows Vista


Technical Data

Positive displacement fan, variable speed
- sound-dampened, max. 84dB(A)
- power consumption: 55kW

Supersonic wind tunnel
- cross section of the measurement section:

- interchangeable walls for measuring section
  1 x straight contour: Ma<1
  2 x de Laval contours: Ma 1,4 and Ma 1,8
Schlieren optics
- halogen lamp with 50 and 100W
- 2 adjustable parabolic mirrors
- adjustable slit diaphragm
- screen for Schlieren optics
Drag bodies
- wedge, double wedge, projectile, rocket
Recommended ambient conditions: 40% rel. humidity at 25C


Dimensions and Weight
LxWxH: 3.500x810x1.715mm (wind tunnel)
LxWxH: 1.710x580x1.450mm (Schlieren optics)
Weight: approx. 1.550kg (wind tunnel and Schlieren optics)
Required for Operation
400V, 50Hz, 3 phases
Scope of Delivery
1 supersonic wind tunnel
3 walls for measuring section
1 Schlieren optics (two piece)
4 drag bodies
1 CD with LabVIEW software + USB cable
1 fan
1 set of instructional material
Order Details

070.17200  HM 172  Supersonic Wind Tunnel with

                                  Schlieren Optics

© 2005 G.U.N.T. Gerätebau GmbH