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).

Investigation of Transient Shock Wave in Supersonic Wind Tunnel

2012 ◽  
Vol 232 ◽  
pp. 228-233
Author(s):  
Behnam Ghadimi ◽  
Mojtaba Dehghan Manshadi ◽  
Mehrdad Bazazzadeh
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Wind Tunnel ◽  
Pressure Ratio ◽  
Wind Tunnels ◽  
Supersonic Wind Tunnel ◽  
Blow Down ◽  
Fortran Code ◽  
Nozzle Contour ◽  
Fluent Software

Wind tunnels are the experimental apparatuses which provide an airstream flowing under controlled conditions so that interesting items in aerospace engineering such as pressure and velocity can be tested. In this work, Shock wave passes through the intermittent blow-down wind tunnel at Mach=2,3,4 has been investigated. The shape of the nozzle contour for a given Mach number was determined using the method of characteristics. For this purpose MATLAB code was developed and this code was verified with Osher’s and AUSM methods, FORTRAN code and FLUENT software was used for these two methods, respectively. Dimensions of different parts of wind tunnel are determined and minimum pressure ratio for the starting condition has been founded using FLUENT software. Good agreement was considered compared with the data from eleven tunnels over their range of Mach number.

The Ludwieg Pressure-Tube Supersonic Wind Tunnel

1963 ◽  
Vol 14 (2) ◽  
pp. 143-157 ◽  
Author(s):  
A. J. Cable ◽  
R. N. Cox
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Nozzle Exit ◽  
High Speed ◽  
Layer Growth ◽  
Stagnation Pressure ◽  
Pressure Tube ◽  
Rarefaction Waves ◽  
Supersonic Wind Tunnel ◽  
Blow Down

SummaryA description is given of a supersonic pressure-tube wind tunnel which has been constructed at A.R.D.E. This is a blow-down tunnel which uses as a reservoir a long tube filled with gas under pressure. A quasi-steady supersonic flow is achieved by expanding in a convergent-divergent nozzle the subsonic flow behind rarefaction waves which propagate down the tube when a diaphragm at the nozzle exit is burst. The theory of the operation of the tunnel is given and calculations are made of the boundary-layer growth along the tube. Pressure-time records were obtained in the tube, and a high speed camera was used to obtain pictures of the flow round a model. Measurements also included a pitot-tube traverse of the nozzle exit, and the Mach number distribution was determined from the ratio of the pitot to the stagnation pressure. Tests showed that, as predicted, a constant stagnation pressure was obtained ahead of the nozzle, and it is considered that a tunnel of this type would be a cheap and simple way of obtaining an intermittent tunnel with adequate running time for many types of test, and capable of operating at a Reynolds number of more than 107 per inch at a Mach number of about 3·5.

scholarly journals Nozzle flows found by the hodograph method. II

1960 ◽  
Vol 1 (3) ◽  
pp. 357-367 ◽  
Author(s):  
T. M. Cherry
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnels ◽  
Perfect Gas ◽  
Supersonic Wind Tunnel ◽  
Hodograph Method ◽  
Sonic Nozzle ◽  
Polytropic Equation ◽  
Nozzle Flows

This is a sequel to a recent paper [1] on the construction by the hodograph method of trans-sonic nozzle-flows of a perfect gas. At the end of that paper it was shown how we can obtain regular flows that are ultimately uniform (as required in the test section of a supersonic wind tunnel), and the object now is to give some quantitative examples of such flows. The gas is supposed to have the polytropic equation of state Pρ−γ = constant, and the calculations have been made for the case γ = 1.4, with the Mach number M = 2.25 at the test section. The results, which are exhibited graphically, are indicative of what may be expected for other supersonic values of M, and it is hoped that they may be significant for the design of wind tunnels.

Design, Fabrication, and Realization of a Supersonic Wind Tunnel for Educational Purposes

2009 ◽  
Vol 37 (4) ◽  
pp. 286-303 ◽  
Author(s):  
Mohammed K. Ibrahim ◽  
A. F. Abohelwa ◽  
Galal B. Salem
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Compressible Flows ◽  
Basic Education ◽  
Design Parameters ◽  
High Tech ◽  
Design Phase ◽  
Supersonic Wind Tunnel ◽  
Design Error ◽  
Standard Textbook

The supersonic wind tunnel is an indispensable facility for basic education in any course that covers compressible flows and one of the main pillars of any aerodynamic laboratory. The introduction of a supersonic wind tunnel at the aerodynamics laboratory of the Aerospace Engineering Department at Cairo University had often been postponed and was hindered by a lack of funds for the purchase of foreign equipment and expertise. Thoughts therefore turned to building such facility instead of buying it, substituting high-tech and complex foreign equipment for locally produced equipment, and ‘thinking out of the box’ to make the most use of available resources, even when this led to some unconventional applications. An extensive scheme for the design, fabrication, and realization of a multi-Mach number ( M = 1.5, 2, and 2.5) supersonic wind tunnel for laboratory experiments is proposed in this paper. The proposed scheme is simple, detailed and multi-level; it starts by utilizing one-dimensional isentropic flow theory for the conceptual design phase and makes full use of computational fluid dynamics at the detailed design phase. This ensured that we had a working design before we embarked on the manufacture of any components, which would have been costly to modify had there been any design error. A parametric study has been carried out for a number of design parameters, using numerical simulations. After the design and fabrication, a number of successful standard textbook experiments, for Mach number 2, were carried out as validation for the proposed scheme. The results showed good agreement with the theoretical predictions.

CVL application for supersonic wind tunnel of blow-down type

1994 ◽  
Author(s):  
T. Fujimoto ◽  
S. Sawaguchi ◽  
K. Hanawa
Keyword(s):  
Wind Tunnel ◽  
Supersonic Wind Tunnel ◽  
Blow Down

Note on the Temperature Transients in a Supersonic “Blow-Down” Wind Tunnel

1958 ◽  
Vol 62 (572) ◽  
pp. 598-599
Author(s):  
L. E. Leavy
Keyword(s):  
United States ◽  
Wind Tunnel ◽  
The United States ◽  
Wind Tunnels ◽  
Blow Down

In recent years, due to the high cost of continuous supersonic wind tunnels, much attention has been focused on the simpler intermittent “blow-down” tunnel.Considerable data has been published on most aspects of the design of this type of equipment and quite a number of large installations have recently been brought into operation in the United States, with even larger numbers currently building both in this country and in the United States.

Control of Blow-Down Wind Tunnel Using Combined Extended and Nonlinear Predictive Filters

2015 ◽  
Author(s):  
Ruixiang Zheng ◽  
Mian Li ◽  
Zhaoguang Wang ◽  
Qiang Zhang
Keyword(s):  
Wind Tunnel ◽  
Control Method ◽  
Wind Tunnels ◽  
State Variables ◽  
Blow Down ◽  
Long Time ◽  
Relationship Of ◽  
Internal Relationship ◽  
Better Than ◽  
Variant System

A blow-down wind tunnel is a typical nonlinear time-variant system facing the coupling of the pressure and temperature during a short duration. The control of blow-down wind tunnels has been discussed for long time and a satisfactory general solution to this problem is still under developing. This paper aims to model the internal relationship of the state variables of the wind tunnel by using thermodynamic theories. With the developed model, a new control method combining Extended Kalman Filter (EKF) together with auxiliary Nonlinear Predictive Filter (NPF) is proposed to improve the control performance of the blow-down wind tunnel controller in terms of precision and robustness. The transient coupling effects between the pressure and temperature are fully considered by the proposed approach. The results both from the simulation and experiments are consistent and prove that the EKF combined together with NPF can work better than previously proposed EKF-based method.

Control of Blow-Down Wind Tunnel Using Combined Extended Kalman and Nonlinear Predictive Filters

2017 ◽  
Vol 139 (4) ◽  
Author(s):  
Ruixiang Zheng ◽  
Mian Li ◽  
Zhaoguang Wang ◽  
Qiang Zhang
Keyword(s):  
Wind Tunnel ◽  
Control Method ◽  
Test Procedure ◽  
Wind Tunnels ◽  
State Variables ◽  
Coupling Effects ◽  
Blow Down ◽  
Long Time ◽  
Short Time ◽  
Relationship Of

A blow-down wind tunnel is a typical nonlinear time-varying system facing the coupling effects between the pressure and temperature during the short-time test procedure. The control of blow-down wind tunnels has been discussed for a long time and a satisfactory general solution to this problem is still of interests. This paper aims to model the internal relationship of the state variables of the wind tunnel by using thermodynamic theories. With the developed model, a new control method combining extended Kalman filter (EKF) together with auxiliary nonlinear predictive filter (NPF) is proposed to improve the control performance of the blow-down wind tunnel controller, in terms of accuracy and robustness. The transient coupling effects between the pressure and temperature are fully considered in the proposed approach. The results from the simulation and experiments are consistent and demonstrate that the controller based on EKF combined together with NPF can work better than previously proposed EKF-based controller.

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