scholarly journals Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne

2020 ◽  
pp. 145-162
Author(s):  
Daniel Kirchheck ◽  
Dominik Saile ◽  
Ali Gülhan
Keyword(s):  
Wind Tunnel ◽  
Operating Conditions ◽  
Wake Flow ◽  
Research Centre ◽  
Test Environment ◽  
Ambient Flow ◽  
Tunnel Model ◽  
Interaction Testing ◽  
German Aerospace ◽  
Exhaust Jet

Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.

scholarly journals Inter-Facility Correlations of Transonic Test Results of the AGARD-C Standard Wind-Tunnel Model

2018 ◽  
Vol 5 (13) ◽  
pp. 26476-26481
Author(s):  
Dijana Damljanović ◽  
Jovan Isaković ◽  
Marko Miloš
Keyword(s):  
Wind Tunnel ◽  
Test Results ◽  
Wind Tunnel Model ◽  
Tunnel Model

Evaluation of an I-box wind tunnel model for assessment of behavioral responses of blow flies

2013 ◽  
Vol 112 (11) ◽  
pp. 3789-3798 ◽  
Author(s):  
Kittikhun Moophayak ◽  
Kabkaew L. Sukontason ◽  
Hiromu Kurahashi ◽  
Roy C. Vogtsberger ◽  
Kom Sukontason
Keyword(s):  
Wind Tunnel ◽  
Behavioral Responses ◽  
Wind Tunnel Model ◽  
Blow Flies ◽  
Tunnel Model

scholarly journals Numerical Investigation of Wind-Tunnel Model Deformations Caused by the Twin-Sting Support System

2010 ◽  
Vol 47 (2) ◽  
pp. 708-714 ◽  
Author(s):  
Roberto Flores ◽  
Enrique Ortega ◽  
Eugenio Oñate
Keyword(s):  
Wind Tunnel ◽  
Numerical Investigation ◽  
Support System ◽  
Wind Tunnel Model ◽  
Tunnel Model

Aerodynamics of a Fixed Ground Plane for a Powered STOL Wind-Tunnel Model

1973 ◽  
Vol 10 (3) ◽  
pp. 137-142
Author(s):  
J. E. Hackett ◽  
J. L. Justice
Keyword(s):  
Wind Tunnel ◽  
Ground Plane ◽  
Wind Tunnel Model ◽  
Tunnel Model

A REVIEW OF PRACTICAL METHODS FOR REDUCING UNDERWATER NOISE POLLUTION FROM LARGE COMMERCIAL VESSELS

2021 ◽  
Vol 154 (A2) ◽  
Author(s):  
R C Leaper ◽  
M R Renilson
Keyword(s):  
Noise Pollution ◽  
Operating Conditions ◽  
Wake Flow ◽  
Underwater Noise ◽  
Data Set ◽  
Marine Life ◽  
Propeller Design ◽  
Widespread Agreement ◽  
Noise Measurements ◽  
Considerable Concern

Underwater noise pollution from shipping is of considerable concern for marine life, particularly due to the potential for raised ambient noise levels in the 10-300Hz frequency range to mask biological sounds. There is widespread agreement that reducing shipping noise is both necessary and feasible, and the International Maritime Organization is actively working on the issue. The main source of noise is associated with propeller cavitation, and measures to improve propeller design and wake flow may also reduce noise. It is likely that the noisiest 10% of ships generate the majority of the noise impact, and it may be possible to quieten these vessels through measures that also improve efficiency. However, an extensive data set of full scale noise measurements of ships under operating conditions is required to fully understand how different factors relate to noise output and how noise reduction can be achieved alongside energy saving measures.

Comparison of Wind Tunnel Airfoil Performance Data With Wind Turbine Blade Data

1992 ◽  
Vol 114 (2) ◽  
pp. 119-124 ◽  
Author(s):  
C. P. Butterfield ◽  
George Scott ◽  
Walt Musial
Keyword(s):  
Wind Tunnel ◽  
Wind Turbine ◽  
Peak Power ◽  
Unsteady Aerodynamics ◽  
Leading Edge ◽  
Operating Conditions ◽  
Performance Data ◽  
Horizontal Axis Wind Turbine ◽  
Force Coefficients ◽  
Basic Fluid

Horizontal axis wind turbine (HAWT) performance is usually predicted by using wind tunnel airfoil performance data in a blade element momentum theory analysis. This analysis assumes that the rotating blade airfoils will perform as they do in the wind tunnel. However, when stall-regulated HAWT performance is measured in full-scale operation, it is common to find that peak power levels are significantly greater than those predicted. Pitch-controlled rotors experience predictable peak power levels because they do not rely on stall to regulate peak power. This has led to empirical corrections to the stall predictions. Viterna and Corrigan (1981) proposed the most popular version of this correction. But very little insight has been gained into the basic cause of this discrepancy. The National Renewable Energy Laboratory (NREL), funded by the DOE, has conducted the first phase of an experiment which is focused on understanding the basic fluid mechanics of HAWT aerodynamics. Results to date have shown that unsteady aerodynamics exist during all operating conditions and dynamic stall can exist for high yaw angle operation. Stall hysteresis occurs for even small yaw angles and delayed stall is a very persistent reality in all operating conditions. Delayed stall is indicated by a leading edge suction peak which remains attached through angles of attack (AOA) up to 30 degrees. Wind tunnel results show this peak separating from the leading edge at 18 deg AOA. The effect of this anomaly is to raise normal force coefficients and tangent force coefficients for high AOA. Increased tangent forces will directly affect HAWT performance in high wind speed operation. This report describes pressure distribution data resulting from both wind tunnel and HAWT tests. A method of bins is used to average the HAWT data which is compared to the wind tunnel data. The analysis technique and the test set-up for each test are described.

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