scholarly journals Investigations in the piston Driven Shock-Tunnel HELM

2019 ◽  
Author(s):  
Ch. Mundt ◽  
C. Selcan ◽  
T. Sander
Keyword(s):  
Shock Tunnel

Post Flight Analysis of SHEFEX I: Shock Tunnel Testing and Related CFD Analysis

2009 ◽  
Author(s):  
Jan Martinez Schramm ◽  
Alexander Wagner ◽  
Jeremy Wolfram ◽  
Klaus Hannemann ◽  
Tarik Barth ◽  
...  
Keyword(s):  
Shock Tunnel ◽  
Cfd Analysis ◽  
Tunnel Testing

Krypton Tagging Velocimetry (KTV) Investigation in the Caltech T5 Reflected-Shock Tunnel

2021 ◽  
Author(s):  
Nick J. Parziale ◽  
Muhammad A. Mustafa ◽  
David Shekhtman ◽  
Joanna M. Austin ◽  
Wesley M. Yu
Keyword(s):  
Shock Tunnel ◽  
Reflected Shock

Development of a Direct-Connect Testing Capability in the HyperTERP Shock Tunnel

2021 ◽  
Author(s):  
Xiu Yi Pee ◽  
Graeme Gillespie ◽  
Stuart J. Laurence
Keyword(s):  
Shock Tunnel

Experimental Study at Hypersonic Shock Tunnel of A 3D Prototyped Scramjet Powered with Hydrogen

2020 ◽  
Author(s):  
Ronaldo Cardoso ◽  
Paulo Toro ◽  
Israel Rêgo ◽  
Thiago Victor Cordeiro Marcos ◽  
Pedro Souza
Keyword(s):  
Experimental Study ◽  
Shock Tunnel ◽  
Hypersonic Shock ◽  
Hypersonic Shock Tunnel

scholarly journals Aerodynamic characteristics of a free-flight scramjet vehicle in shock tunnel

2021 ◽  
Vol 62 (7) ◽  
Author(s):  
Marie Tanno ◽  
Hideyuki Tanno
Keyword(s):  
System Analysis ◽  
Force Measurement ◽  
Prediction Interval ◽  
Angular Acceleration ◽  
Aerodynamic Characteristics ◽  
Measurement Precision ◽  
Shock Tunnel ◽  
Free Flight ◽  
Vehicle Model ◽  
Aerodynamic Test

Abstract A multi-component aerodynamic test for an airframe-engine integrated scramjet vehicle model was conducted in the free-piston shock tunnel HIEST. A free-flight force measurement technique was applied to the scramjet vehicle model named MoDKI. A new method using multiple piezoelectric accelerometers was developed based on overdetermined system analysis. Its unique features are the following: (1) The accelerometer’s mounting location can be more flexible. (2) The measurement precision is predicted to be improved by increasing the number of accelerometers. (3) The angular acceleration can be obtained with single-axis translational accelerometers instead of gyroscopes. (4) Through the averaging process of the multiple accelerometers, model natural vibration is expected to be mitigated. With eight model-onboard single-axis accelerometers, the three-component aerodynamic coefficients (Drag, Lift, and Pitching moment) of MoDKI were successfully measured at the angle of attack from 0.7 to 3.4 degrees under a Mach 8 free-stream test flow condition. A linear regression fitting revealed a 95% prediction interval as the measurement precision of each aerodynamic coefficient. Graphical abstract

Free-flight measurement technique in the free-piston high-enthalpy shock tunnel

2014 ◽  
Vol 85 (4) ◽  
pp. 045112 ◽  
Author(s):  
H. Tanno ◽  
T. Komuro ◽  
K. Sato ◽  
K. Fujita ◽  
S. J. Laurence
Keyword(s):  
Measurement Technique ◽  
Shock Tunnel ◽  
Free Flight ◽  
Free Piston ◽  
High Enthalpy ◽  
Flight Measurement ◽  
High Enthalpy Shock Tunnel
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