Investigation of Variable Mach Number Wind Tunnel with Symmetric Sliding Block Nozzles

2022 ◽  
Author(s):  
V. Vijayakrishnan ◽  
Prateek Kishore ◽  
Muruganandam T. M.
Keyword(s):  
Mach Number ◽  
Wind Tunnel

Investigations on Aerodynamic Loading Limits of Subsonic Compressor Tandem Cascades: Midspan Flow

2013 ◽  
Author(s):  
Charlotte Hertel ◽  
Christoph Bode ◽  
Dragan Kožulović ◽  
Tim Schneider
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Numerical Simulations ◽  
Pressure Distribution ◽  
Large Range ◽  
Pressure Rise ◽  
Transition Model ◽  
Diffusion Factor ◽  
Aerodynamic Loading ◽  
Tandem Cascades

An optimized subsonic compressor tandem cascade was investigated experimentally and numerically. Since the design aims at incompressible applications, a low inlet Mach number of 0.175 was used. The experiments were carried out at the low speed cascade wind tunnel at the Technische Universität Braunschweig. For the numerical simulations, the CFD-solver TRACE of DLR Cologne was used, together with a curvature corrected k-ω turbulence model and the γ-Reθ transition model. Besides the incidence variation, the aerodynamic loading has also been varied by contracting endwalls. Results are presented and discussed for different inlet angles and endwall contractions: pressure distribution, loss coefficient, turning, pressure rise, AVDR and Mach number. The comparison of experimental and numerical results is always adequate for a large range of incidence. In addition, a comparison is made to an existing high subsonic tandem cascade and conventional cascades. For the latter the Lieblein diffusion factor has been employed as a measure of aerodynamic loading to complete the Lieblein Chart of McGlumphy [1].

Dynamic Inlet Simulation Demonstration for Airframe-Propulsion Integration Using HPCMP CREATE™-AV Kestrel

2017 ◽  
Author(s):  
Jason B. Klepper ◽  
James R. Sirbaugh ◽  
Milt W. Davis
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Systems Design ◽  
Computational Results ◽  
Military Aircraft ◽  
Fighter Aircraft ◽  
Inlet System ◽  
Weapon Systems ◽  
Dynamic Hybrid

The purpose of an aircraft inlet system is to capture airflow from the free-stream and deliver it to an engine at the appropriate Mach number for that system. To meet design constraints, modern fighter aircraft have complex inlets with multiple turns that generally lead to both total pressure and swirl distortion at the engine face. These flow distortions can lead to reduced system performance, operability, and durability introducing issues in the overall success of the weapons system performing its mission. Therefore the integration of the airframe, inlet, and propulsion system is a key design issue in the development of military aircraft. The purpose of this paper is to demonstrate the dynamic (hybrid RANS/DDES) simulation capabilities of the HPCMP CREATE™-AV Kestrel tools by application to a sub-scale airframe/inlet system for a current military aircraft. The computational results were compared to wind tunnel results at various Mach number, angles of attack, angles of sideslip, and corrected flow rates. The inlet pressure recovery and distortion intensities for each case compared well to wind tunnel results. By comparing the computational results and wind tunnel test results, the applicability of these tools to future weapon systems design and development can be assessed.

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).

The Effect of Canard to the Aerodynamic Behavior of Blended Wing Body Aircraft

2012 ◽  
Vol 225 ◽  
pp. 38-42
Author(s):  
Zurriati Mohd Ali ◽  
Wahyu Kuntjoro ◽  
Wisnoe Wirachman
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Aerodynamic Characteristic ◽  
Lift Coefficient ◽  
Aerodynamic Characteristics ◽  
Moment Coefficient ◽  
Subsonic Wind Tunnel ◽  
Setting Angle ◽  
Blended Wing Body ◽  
The Moment

This paper presents a study on the effect of canard setting angle on the aerodynamic characteristic of a Blended Wing Body (BWB). Canard effects to BWB aerodynamic characteristics are not widely investigated. Hence the focus of the study is to investigate the variations of lifts, drags and moments when the angles of attack are varied at different canard setting angles. Wind tunnel tests were performed on BWB aircraft with canard setting angles,  ranging from -20˚ to 20˚. Angles of attack,  were varied from -10˚ to 10˚. Aspect ratio and canard planform area were kept fixed. All tests were conducted in the subsonic wind tunnel at Universiti Teknologi MARA, at Mach number of 0.1. The streamlines flow, at the upper surface of the canard was visualized using mini tuft. Result shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The results obtained in this research will be of importance to the understanding of aerodynamic behavior of BWB employing canard in its configuration.

Experimental Investigation of Pressure Side Flow Separation on the T106C Airfoil at High Suction Side Incidence Flow

2016 ◽  
Author(s):  
Stephan Stotz ◽  
Reinhard Niehuis ◽  
Yavuz Guendogdu
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Separation Bubble ◽  
Suction Side ◽  
Pressure Side ◽  
Blade Passage ◽  
Wide Range ◽  
Profile Losses ◽  
Exit Mach Number ◽  
Side Flow

The objective of this work is to study the influence of a pressure side separation bubble on the profile losses and the development of the bubble in the blade passage. For the experimental investigations the T106 profile is used, with an increased loading due to an enlarged pitch to chord ratio from 0.799 to 0.95 (T106C). The experiments were performed at the high-speed cascade wind tunnel of the Institute of Jet Propulsion at the University of the Federal Armed Forces Munich. The main feature of the wind tunnel is to vary Reynolds and Mach number independently to achieve realistic turbomachinery conditions. The focus of this work is to determine the influence of a pressure side separation on the profile losses and hence the robustness to suction side incidence flow. The cascade is tested at four incidence angles from 0° to −22.7° to create separation bubbles of different sizes. The influence of the Reynolds number is investigated for a wide range at constant exit Mach number. Therefore a typical exit Mach number for low pressure turbines in the range of 0.5–0.8 is chosen in order to consider compressible effects. Furthermore, two inlet turbulence levels of about 3% and 7.5% have been considered. The characteristics of the separation bubble are identified by using the profile pressure distributions, whereas wake traverses with a five hole probe are used to determine the influence of the pressure side separation on the profile losses. Further, time-resolved pressure measurements near the trailing edge as well as single hot wire measurements in the blade passage are conducted to investigate the unsteady behavior of the pressure side separation process itself and also its influence on the midspan passage flow.

Modification of Transonic Blowdown Wind Tunnel to Produce Oscillating Freestream Mach Number

AIAA Journal ◽  
2011 ◽  
Vol 49 (11) ◽  
pp. 2555-2563 ◽  
Author(s):  
Kyle Gompertz ◽  
Christopher Jensen ◽  
Pradeep Kumar ◽  
Di Peng ◽  
James W. Gregory ◽  
...  
Keyword(s):  
Mach Number ◽  
Wind Tunnel
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