Investigation of Transonic Ludwieg Tubes Part I Starting Process in the Case of an Upstream Valve
スポンサーリンク
概要
- 論文の詳細を見る
Among many different types of transonic wind tunnels, a transonic Ludwieg tube is the most suitable facility for very high Reynolds number transonic wind tunnel testing. At present, however, the transonic starting process and starting time of this short duration test facility are not well clarified. In the present paper, the starting process of transonic Ludwieg tube with a quick-opening valve upstream of the transonic test section was experimentally investigated over a range of plenum chamber volumes and flow rates using a plenum exhaust system. As the result, it has been shown that a steady and uniform flow in the test section is established when the mass flow rate through the porous wall of the test section becomes equal to that through the plenum exhaust system. Based on the experimental results, wave diagrams showing the starting process were presented, and the flow mechanism of the starting process was clarified.
- 一般社団法人日本機械学会の論文
著者
-
MATSUO Kazuyasu
Graduate School of Engineering, Sciences, Kyushu University
-
Nagatake Minoru
Faculty Of Engineering Oita University
-
Matsuo Kazuyasu
Graduate School Of Eng. Sciences Kyushu University
-
KAGE Kazuyuki
Faculty of Engineering, Oita University
-
KAWAGOE Sigetoshi
Graduate School of Engineering Sciences, Kyushu University
-
Kage Kazuyuki
Faculty Of Engineering Oita University
-
KAWAGOE Sigetoshi
Kyushu University
関連論文
- Investigations of Mach Reflection of a Shock Wave : 4th Report, The Transition between Regular and Mach Reflections
- Investigations of Mach Reflection of a Shock Wave : 3rd Report, Strength of a Reflected Shock Wave
- Investigations of Mach Reflection of a Shock Wave : 2nd Report, Shape of a Reflected Shock Wave
- Studies of Condensation Shock Waves : 2nd Report, Relation between Condensation Shock Wave and Condensation Zone
- Investigations of Mach Reflection of a Shock Wave : Part 1,Configurations and Domains of Shock Reflection
- Relation between Condensation and Thermal Choking in an Unsteady Subsonic Flow
- Effects of Condensing Flow on an Oblique Shok Wave in a Supersonic Nozzle
- Oscillations of Laval Nozzle Flow with Condensation : Part 2, On the Mechanism of Oscillations and their Amplitudes
- Oscillations of Laval Nozzle Flow with Condensation : Part 1,On the Range of Oscillations and their Frequencies
- Investigations of Transonic Ludwieg Tubes : 4th Report, Effects of Flow Mach Number in Supply Tube on Starting Process of Test Section
- Investigations of Transonic Ludwieg Tubes : Part3 Effects of Plenum Exhaust System on Starting Process of Tunnel Test Section
- Investigations of Transonic Ludwieg Tubes Part 2 Starting Process in the Case of a Downstream Valve
- Investigation of Transonic Ludwieg Tubes Part I Starting Process in the Case of an Upstream Valve
- Modified Diffusion Model of Pseudo-Shock Waves Considering Upstream Boundary Layers
- Investigation of Supersonic Air Ejectors : Part 2,Effects of Throat-Area-Ratio on Ejector Performance
- Investigation of Supersonic Air Ejectors : Part 1. Performance in the Case of Zero-Secondary Flow
- Investigation of the Starting Process of a Supersonic Wind Tunnel
- Choking Phenomena of Flows in a Shock Tube
- The Error in Measuring an Accelerated Flow Velocity by a Spark Tracer Method
- An Investigation of Transonic Ludwieg Tubes : 5th Report, Effects of Valve Opening Time on Starting Process of Test Section : Series B : Fluid Engineering, Heat Transfer, Combustion, Power, Thermophysical Properties
- The Interaction of a Reflected Shock Wave with the Contact Region in a Shock Tube
- The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube
- Flow Unsteadiness by Weak Normal Shock Wave/Turbulent Boundary Layer Interaction in Internal Flow
- Extension of the Steady Flow Duration of a Ludwieg Tube Using a Reservoir-orifice Method : Part11, Case of Orifices with Variable Opening Area
- Post-Shock Expansion Phenomenon Caused by Normal Shock/Turbulent Boundary Layer Interaction
- Self-excited Oscillations of Supersonic Flow in a Sudden Enlargement of a Duct
- Pseudo-Shock Waves in a Divergent Channel
- Reduction of Impulsive Noise Caused by Unsteady Compression Wave
- Total Pressure Loss in Supersonic Nozzle Flows with Condensation (Numerical Analyses)
- Studies of Condensation Shock Waves : Part 1, Mechanism of their Formation
- Numerical Study of Compression Waves Produced by High-Speed Trains Entering a Tunnel : Effects of Shape of Hood
- Oscillation of Primary Flow of a Supersonic Air Ejector
- On the Double-vacuurn Phenomenon of a Supersonic Air Ejector
- Investigation of the Slipstream in Mach Reflections