Abstract
This study describes theory and methods for developing detonation-driven shock tunnels in hypervelocity test facilities. The primary concept and equations for high-enthalpy shock tunnels are presented first to demonstrate the unique advantage of shock tubes for aerodynamic ground-based testing. Then, the difficulties in simulating flight conditions in hypervelocity shock tunnels are identified, and discussed in detail to address critical issues underlying these difficulties. Theory and methods for developing detonation drivers are proposed, and relevant progress that has advanced the state of the art in large-scale hypersonic test facilities is presented with experimental verifications. Finally, tailored conditions for detonation-driven shock tunnels are described, laying a solid foundation to achieve long test duration. This interface-matching key issue encountered in developing shock tunnels has been investigated for decades, but not solved for detonation drivers in engineering applications.
Highlights
Great success has been achieved in aeronautics and astronautics since the first flight powered with an engine was made successfully by the Wright brothers in 1903
The primary concept and equations for high-enthalpy shock tunnels are presented first to demonstrate the unique advantage of shock tubes for aerodynamic ground-based testing
The free-piston driver works well for shock tunnels to produce high-enthalpy flows with a short test duration, but has its limitation in meeting the need from large-scale hypersonic test facilities which would operate for long test duration
Summary
Great success has been achieved in aeronautics and astronautics since the first flight powered with an engine was made successfully by the Wright brothers in 1903. Air-heating wind tunnels are widely used all over the world, and test flows with Mach numbers as high as 7 can be generated if the sound speed is simulated to be that at flight altitudes.
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