A STUDY OF SHORT-TIME, LOW-PRESSURE RESPONSE IN A TRANSDUCER SYSTEM.
Test and evaluation rept.,
NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER WASHINGTON D C DEPT OF AERODYNAMICS
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Existing theoretical equations were correlated with experimental pressure-time responses in the 0.1 mmHg to 3.0 mmHg pressure range in short-time response transducer systems. Experimental investigation confirmed predicted trends but the equations required modifications to account for end effects which were neglected in the original derivations. The prediction errors of these modified equations were within an acceptable range. The results provide system design criteria for free flight instrumented models in hypersonic tunnel applications. Author
- Test Facilities, Equipment and Methods