Stennett et al., 2020 - Google Patents
The X3R Free-Piston Reflected Shock Tunnel: Australia's New Large-Scale, Long-Duration Hypersonic Testing CapabilityStennett et al., 2020
- Document ID
- 7565638173726899406
- Author
- Stennett S
- Gildfind D
- Jacobs P
- Morgan R
- James C
- Toniato P
- Publication year
- Publication venue
- 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference
External Links
Snippet
X3R is a new, large-scale free-piston driven reflected shock tunnel designed and operated at the University of Queensland, Australia. The facility is a derivative of the X3 super-orbital expansion tube, which uses a combination of new and pre-existing hardware. It is capable of …
- 230000035939 shock 0 title abstract description 40
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies
- Y02T50/67—Relevant aircraft propulsion technologies
- Y02T50/671—Measures to reduce the propulsor weight
Similar Documents
Publication | Publication Date | Title |
---|---|---|
Schmidt et al. | Optical measurements of muzzle blast | |
Hannemann et al. | The high enthalpy shock tunnel Göttingen of the German aerospace center (DLR) | |
Hannemann et al. | Free piston shock tunnels HEG, HIEST, T4 and T5 | |
Hannemann et al. | Recent extensions to the high enthalpy shock tunnel Göttingen (HEG) | |
Stennett et al. | The X3R Free-Piston Reflected Shock Tunnel: Australia's New Large-Scale, Long-Duration Hypersonic Testing Capability | |
Stalker | The free-piston shock tube | |
Collen et al. | Commissioning of the t6 stalker tunnel | |
Prislin | Free-flight and free-oscillation techniques for wind-tunnel dynamic-stability testing | |
Verma et al. | Gas-density effects on dual-bell transition behavior | |
PlESIK et al. | Rocket-exhaust impingement on a flat plate at high vacuum. | |
Toniato et al. | Full free-stream Mach 12 scramjet testing in expansion tubes | |
Johnson | The Design and Implementation of a Supersonic Indraft Tube Wind Tunnel for the Demonstration of Supersonic Flows | |
Myrabo et al. | Apollo Lightcraft Project | |
Verma et al. | Cold gas dual-bell tests in high-altitude simulation chamber | |
Hannemann et al. | Shock tunnel free flight force measurements using a complex model configuration | |
Landsbaum | Contour nozzles | |
Kim et al. | Drag and heat-flux assessment of hypersonic flow on an asymmetric blunt shaped body | |
Buttsworth et al. | Development of a Ludwieg tube with free piston compression heating for scramjet inlet starting experiments | |
Kulkarni et al. | Counterflow drag reduction studies for a blunt cone in high enthalpy flow | |
Mizukaki | Visualization and force measurement of high-temperature, supersonic impulse jet impinging on baffle plate | |
US3478583A (en) | Plasma driven shroud wind tunnel | |
Naumann et al. | Ram accelerator ballistic range concept for softly accelerating hypersonic free-flying models | |
CN116202367B (en) | Ballistic target based on electromagnetic ejection auxiliary driving secondary light air cannon | |
Dionisio et al. | Aerodynamic wind-tunnel test of a ramjet projectile | |
Blanks et al. | Calibration tests of AEDC free-piston shock tunnel |