Numerical Research on the NS-SDBD Control of a Hypersonic Inlet in Off-Design Mode
Victor R. Soloviev
Round 1
Reviewer 1 Report
In this paper, the effect of NS-SDBD on the performance of hypersonic inlet was investigated using numerical analysis. The author simply solved the RANS equation with the energy source term given by phenomenological method. In the introduction, the author did not introduce any published paper on NS-SDBD using the phenomenological method (only conference papers using this method). Therefore, research works using this method seem to be rare. However, if the results of the paper are sufficiently accurate, this method can be a useful approach to understanding that kind of flow control mechanism.
Some explanations and revisions are necessary :
1) Temporal accuracy is important to observe the nanosecond pulse discharge effect. In Figure 4, the pressure wave propagation speed (speed of sound) was confirmed. However, peak pressure values, flow speeds, and temperature changes have not been verified. Further verification or reasonable explanation is required.
2) The pulse discharge duration is the same in all cases, which is 50 ns. Therefore, the higher the pulse discharge frequency, the greater the energy supply to the flow. That is why we have a greater pressure ratio with a higher frequency in Figure 11. To observe only the frequency effect, the amount of energy used for pulse discharge must be kept constant. Alternatively, to observe the effect of the amount of energy, you can keep the frequency constant and change the amount of energy instead.
3) In Figures 11 and 14, information on pressure fluctuations cannot be obtained from simple average values. Please notify the fluctuation interval in the figures.
Author Response
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Author Response File: 
Author Response.pdf
Reviewer 2 Report
Comments for author File: Comments.pdf
Author Response
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Author Response File: Author Response.pdf
Round 2
Reviewer 1 Report
The authors answered all questions appropriately and revised the manuscript well.
