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Dielectric barrier discharge (dbd) plasma actuators thrust-measurement methodology incorporating new anti-thrust hypothesis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Laun, Matthew C. Ashpis, David E. |
| Copyright Year | 2014 |
| Description | We discuss thrust measurements of Dielectric Barrier Discharge (DBD) plasma actuators devices used for aerodynamic active flow control. After a review of our experience with conventional thrust measurement and significant non-repeatability of the results, we devised a suspended actuator test setup, and now present a methodology of thrust measurements with decreased uncertainty. The methodology consists of frequency scans at constant voltages. The procedure consists of increasing the frequency in a step-wise fashion from several Hz to the maximum frequency of several kHz, followed by frequency decrease back down to the start frequency of several Hz. This sequence is performed first at the highest voltage of interest, then repeated at lower voltages. The data in the descending frequency direction is more consistent and selected for reporting. Sample results show strong dependence of thrust on humidity which also affects the consistency and fluctuations of the measurements. We also observed negative values of thrust or "anti-thrust", at low frequencies between 4 Hz and up to 64 Hz. The anti-thrust is proportional to the mean-squared voltage and is frequency independent. Departures from the parabolic anti-thrust curve are correlated with appearance of visible plasma discharges. We propose the anti-thrust hypothesis. It states that the measured thrust is a sum of plasma thrust and anti-thrust, and assumes that the anti-thrust exists at all frequencies and voltages. The anti-thrust depends on actuator geometry and materials and on the test installation. It enables the separation of the plasma thrust from the measured total thrust. This approach enables more meaningful comparisons between actuators at different installations and laboratories. The dependence on test installation was validated by surrounding the actuator with a large diameter, grounded, metal sleeve. |
| File Size | 1209155 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150006708 |
| Archival Resource Key | ark:/13960/t8cg4qf5p |
| Language | English |
| Publisher Date | 2014-01-13 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Electric Potential Actuators Performance Tests Plasmas Physics Consistency Dielectrics High Voltages Boundary Layer Control Thrust Measurement Humidity Flow Distribution Plasma Frequencies Aerodynamic Characteristics Alternating Current Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
