Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel

2015 ◽  
Author(s):  
Klaus Hannemann ◽  
Jan Martinez Schramm ◽  
Sebastian Karl ◽  
Stuart J. Laurence
Keyword(s):  
Large Scale ◽  
Shock Tunnel ◽  
Free Flight ◽  
Flight Testing ◽  
Scramjet Engine

Extended Shock-Tunnel Operation for Aeroballistics Free-Flight Testing

2012 ◽  
pp. 457-463
Author(s):  
F. Seiler ◽  
M. Bastide ◽  
J. Srulijes ◽  
J. -L. Striby ◽  
P. Wey
Keyword(s):  
Shock Tunnel ◽  
Free Flight ◽  
Flight Testing

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

Free-Flight Testing in Support of the Mars Science Laboratory Aerodynamics Database

2006 ◽  
Vol 43 (2) ◽  
pp. 293-302 ◽  
Author(s):  
Jeff Brown ◽  
Leslie Yates ◽  
David Bogdanoff ◽  
Gary Chapman ◽  
Mark Loomis ◽  
...  
Keyword(s):  
Science Laboratory ◽  
Free Flight ◽  
Flight Testing ◽  
Mars Science Laboratory

Evaluation of Large-Scale Wing Vortex Wakes from Multi-Camera PIV Measurements in Free-Flight Laboratory

2008 ◽  
pp. 377-394 ◽  
Author(s):  
Carl F. v. Carmer ◽  
André Heider ◽  
Andreas Schröder ◽  
Robert Konrath ◽  
Janos Agocs ◽  
...  
Keyword(s):  
Large Scale ◽  
Free Flight ◽  
Piv Measurements
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