the Creative Commons Attribution 4.0 License.
the Creative Commons Attribution 4.0 License.
Design and Rocket Deployment of a Trackable Pseudo-Lagrangian Drifter based Meteorological Probe into the Lawrence/Linwood EF4 Tornado and Mesocyclone on 28 May 2019
Reed Timmer
Mark Simpson
Sean Schofer
Curtis Brooks
Abstract. A custom lightweight, miniaturized, and trackable meteorological probe was launched by a model rocket into the inflow region near an EF4, long-tracked tornado south of Lawrence, Kansas, on 28 May 2019 and sampled tornado core flow. The rocket reached apogee at 439 m AGL, releasing the "pseudo-Lagrangian drifter" by parachute directly into the tornado vortex. The probe reached a velocity of 85.1 m s-1 in the first revolution around the tornado, measured a pressure deficit of -113.5 hPa at 475 m MSL, and sampled a tornadic updraft of 65.0 m s-1. The probe then transitioned to an environment exhibiting more tilted ascent above an altitude of 4,300 m MSL at speeds up to 84.0 m s-1 to a maximum altitude of 11,914 m MSL. 1 Hz pressure, temperature, relative humidity, GPS, acceleration, gyroscope, and magnetometer data for the flight were transmitted in real-time to a ground station until the probe landed 51 km northeast of the launch position. The probe was recovered without damage, which is attributed to the pseudo-Lagrangian Drifter design, and then higher resolution 10 Hz data was downloaded. This novel deployment method and design facilitate data collection in real-time from within tornadoes, the mesocyclone, and downdraft without requiring the probes to be recovered or for researchers to enter the circulation to deploy equipment.
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Reed Timmer et al.
Status: final response (author comments only)
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RC1: 'Comment on egusphere-2023-781', Anonymous Referee #1, 27 Jun 2023
Design and Rocket Deployment of a Trackable Pseudo-Lagrangian Drifter based Meteorological Probe into the Lawrence/Linwood EF4 Tornado and Mesocyclone on 28 May 2019
Author(s): Reed Timmer et al.General comments
The manuscript presents the design and deployment of a meteorological probe for sampling the tornado flow. The study shows that lightweight meteorological probes launched by rockets can allow measurements of wind and thermodynamic conditions of the tornado flow. So far this type of measurements were very hard to obtain due to strong wind and strong pressure gradients associated with the tornado.
The paper is within the scope of the journal and is addressing a relevant scientific question regarding the measurement of wind and thermodynamics in tornadoes that will allow a better understanding of their impact. Thus, a novel method is presented to measure directly the three-dimensional wind and thermodynamics inside a tornado. The description of the meteorological probe and the rocket is complete allowing their reproduction by fellow researchers. Furthermore, the title and the abstract are clear and concise.
Specific comments
- I think a short explanation regarding the pseudo-Lagrangian drifters will be helpful for the readers.
- Lines 101-102: This is not very clear for a general reader as the sentence is quite technical: “Using quaternions from the IMU and the sensor-fusion, the Tait-Bryan angles for pitch, yaw, and roll (as is used in aircraft orientation) were derived”.
- The future design and sensors changes should be included in a separate sections (“Future work”).
Technical corrections
Lines 47-52: This paragraph consist of one sentence. I think it could be integrated with the next two paragraphs.
Line 67: “[…]of Markowski et al. (2018) and Bartos et al. (2022)”.
Line 159: :”Federal Aviation Administration (2022) […].
Line 167: “[…] (National Association of Rocketry, 2022a, b).”
Line 185: “-20oC”.
Line 196: Time should be in UTC.
Citation: https://doi.org/10.5194/egusphere-2023-781-RC1 -
AC1: 'Reply on RC1', Mark Simpson, 10 Jul 2023
The authors appreciate the time and effort that Anonymous Referee #1 has dedicated to providing valuable feedback on our manuscript to improve the work. We are grateful for your insightful comments on our paper.
Please note that the below corrections have been made to the manuscript and will be uploaded later as per the AMT review process for an external preprint.
I think a short explanation regarding the pseudo-Lagrangian drifters will be helpful for the readers.
The following sentence has been added to the introduction “A pseudo-Lagrangian drifter is a sufficiently miniaturized, instrumented probe that is intended to move along with the wind flow, such that the speed of the probe is very close to the wind speed of the air in which it is embedded.”
Lines 101-102: This is not very clear for a general reader as the sentence is quite technical: “Using quaternions from the IMU and the sensor-fusion, the Tait-Bryan angles for pitch, yaw, and roll (as is used in aircraft orientation) were derived”.
Changed to: “Using the IMU sensor-fusion of the magnetometer, accelerometer, and gyroscope, pitch, yaw, and roll angles were derived.”
The future design and sensors changes should be included in a separate sections (“Future work”).
All references to future work/changes within the body of the text have been moved to the section “Lessons Learned/Future Work”.
Technical corrections
Lines 47-52: This paragraph consists of one sentence. I think it could be integrated with the next two paragraphs.
Restructured from 3 paragraphs to 2, to read as follows:
“Over the past two decades, field experiments such as VORTEX, VORTEX2, and Project TORUS have improved the understanding of supercells, tornadoes, and particularly tornado environments using mobile Doppler radar (X-, W-, Ka-band), in situ ground-based probes, balloons, mobile mesonets, and Unmanned Aerial Systems (UAS) (Straka et al., 1996; Bluestein et al., 2003; Wakimoto et al., 2003; Bluestein et al., 2004; Samaras and Lee, 2004; Blair et al., 2008; Weiss and Schroeder, 2008; Karstens et al., 2010; Kosiba and Wurman, 2010, 2013; Wakimoto et al., 2011; Wurman et al., 2012; Tanamachi et al., 2013; Winn et al., 1999; Samaras, 2004; Pazmany et al., 2013; Frew et al., 2020; Houston et al., 2020; Markowski et al., 2018). However, the UAS technology of Project TORUS is not intended for direct measurements inside of a tornado core flow (Frew et al., 2020; Houston et al., 2020).
Mobile radars are mainly limited to measuring horizontal wind of storms and tornadoes, with the vertical component being inferred due to inclined measurements unless the measurements are taken vertically from dangerous positions inside a tornado. Multiple-elevation mobile radar data coupled with photogrammetry techniques and or ground-based wind measurements have successfully derived information on the three-dimensional winds of tornadoes (Wakimoto et al., 2011; Kosiba and Wurman, 2010, 2013; Tanamachi et al., 2013). However, mobile radar-based analyses of winds inside tornadoes using multiple elevations are limited in spatial and temporal resolution, range and provide limited information on the thermodynamics of tornadoes (Markowski et al., 2018).”
Line 67: “[…]of Markowski et al. (2018) and Bartos et al. (2022)”.
Corrected
Line 159: :”Federal Aviation Administration (2022) […].
Corrected
Line 167: “[…] (National Association of Rocketry, 2022a, b).”
Corrected
Line 185: “-20oC”.
Corrected
Line 196: Time should be in UTC.
Corrected
Citation: https://doi.org/10.5194/egusphere-2023-781-AC1
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AC2: 'Response to Anonymous Referee #2', Mark Simpson, 10 Jul 2023
Please note, this is a response to the comments from Anonymous Referee #2 provided in the "Access review with quick reports" phase of review.
The authors appreciate the time and effort that Anonymous Referee #2 has dedicated to providing valuable feedback on our manuscript to improve the work. We are grateful for your insightful comments on our paper.
Overall a good paper that accomplishes what it promises – it describes the rocket-launched drifter and presents results. Below are several minor comments:
1. The term “pseudo-Lagrangian drifter” is applied because the path of the drifter is assumed to be the path of the wind. The sink rate of the drifter could be determined and used to derive a better estimate of the wind. Why was this not considered?
The authors considered correcting the “W” wind component for the sink rate of the pseudo-Lagrangian drifter. There are a number of factors that impact the sink rate, including pressure perturbation within the tornado vortex and updraft, altitude due to air density, and varying sink rates within the downdraft, all of which would be dependent on temperature too. Rather than adding a number of corrections to adjust for the sink rate which could also interact with the temperature and thermal lag correction or be co-dependent, we concluded that a more conservative approach was to specify the range of 4-6 m s-1 calculated for the air densities encountered rather than having the “W” component potentially higher than experienced by the probe.
2. The following paper also describes a pseudo-Lagrangian drifter designed to operate in severe storms. This reference did not deploy into a tornado, but does include results from the storm environment:
Sara Swenson, Brian Argrow, Eric Frew, Steve Borenstein, Jason Keeler. “Development and Deployment of Air-Launched Drifters from Small UAS.” Sensors. 19(9): 2149, May 2019.
This reference has been added: “Using pseudo-Lagrangian drifters for infiltrating thunderstorms and supercells with sensors has been accomplished using a dual-balloon approach (Markowski et al., 2018) and a single-balloon approach where the balloon is filled with helium during flight (Swenson et al., 2019)”
3. The paper would be improved by moving comments about future design elements into a new section on Lessons Learned / Future Work. The current style of describing improvements and new designs in the main body weakens the paper and downplays the significance of these results.
All references to future work/changes within the body of the text have been moved to the section “Lessons Learned/Future Work”.
Citation: https://doi.org/10.5194/egusphere-2023-781-AC2 -
RC2: 'Comment on egusphere-2023-781', Anonymous Referee #3, 28 Sep 2023
Journal Review: Design and Rocket Deployment of a Trackable Pseudo-Lagrangian Drifter based Meteorological Probe into the Lawrence/Linwood EF4 Tornado and Mesocyclone on 28 May 2019
Authors: Reed Timmer, Mark Simpson, Sean Schofer, and Curtis Brooks
Submitted to EGUsphere
Summary:
The manuscript describes a new probe sensor designed to be launched via model rocket into severe convection, with a focus on deployments into tornadoes. The paper outlines the need for such observations by highlighting a lack of direct observations in tornadoes, and describes in some detail the new probe design and delivery mechanism. The manuscript then provides a case study where the probe was successfully deployed into an EF4 tornado, and show cases the data collected.
The observations presented here are novel and worthy of publication. I commend the authors for their efforts to push the limits of observational technology and data sets. The study would have benefited from additional observations such as mobile radar observations or a more detailed radar analysis in a 3-dimensional sense to place the observations in context to the larger storm, but do not negate the benefit of documenting the results. However, I would strongly suggest that the authors remove all discussion and presentation of thermodynamic data from the probe given several critical concerns (detailed below) over the ability of the probe to accurately represent the thermodynamic environment. If the authors wish to keep the thermodynamic observations in the manuscript, there are significant questions that must be addressed and documented in the manuscript. The observations of the kinematic structure are however valid and important for documentation, and represent a novel exploration into the kinematic structure of tornadoes.
I have a number of comments for the authors consideration, broken into three main sections. Overall comments are general observations over the entirety of the paper or large scale themes. Major comments are significant questions or issues that I see with the manuscript, either in structure of the paper or the science being presented. Minor comments are generally minor things, and to some extent are personal preferences, but are generally things that I believe would improve the paper.
Overall comments:
1). There are numerous instances throughout the manuscript where paragraphs are single sentences. I would encourage the authors to consolidate similar themed statements into single coherent paragraphs rather than breaking them apart into multiple paragraphs. This may just be an artifact of the preprint, but it should be addressed either way.
2). The current study describes the observations collected by the probe and compares it with a single radar scan (KTWX, 0.7 degree elevation). While this is important, the radar scan takes places before the launch of the rocket and there is no additional analysis presented. I think the study would benefit considerably by additional radar observations throughout the nearly 30 min flight time of the probe, as well as exploring higher elevation angles to provide deeper context to the observations. While the observations themselves are novel, placing them into the context of the larger storm enhances the scientific value and allows for future work to build off of. I encourage the authors to expand the analysis and discussion section by utilizing additional radar data.
Major comments:
1). Line 24-26: the final statement of this paragraph is slightly abrupt and out of place given that the manuscript has not mentioned the probes in the body of the text yet (only in the abstract), and requires a bit of a rework. This should be moved to the end of the introduction section after setting up the “problem”, which is a lack of direct observations inside the tornado vortex. A final paragraph such as the following would suffice:
“Given the above mentioned studies, it is clear that there is a notable lack of direct observations inside or near the tornado vortex. To address this observational need, the present study describes a new, miniaturized, pseudo-lagrangian sensor deployed from a low-cost surface based model rocket that is capable of obtaining these observations inside the circulation. The design of this sensor as well as a case study showing its use is presented here.”
With the above you could remove, or incorporate, the current final paragraph of the introduction with the above suggested paragraph. This change, along with other suggestions, would streamline the flow of the introduction sections and lead into the methodology.
2). Lines 68-74, this is great information but belongs in the discussion of the actual sensor. This should be moved to section 2 under methodology. This is simply a major comment as it involves restructuring the paper to a degree.
3). I have numerous questions and concerns regarding the probe design itself and the ability of the probe to accurately represent the (thermodynamic) environment in which it is travelling. I will list each here.
- The authors state on line 121 that a conformal coating was added to the probe in order to protect the sensors from damage. This however is adding a barrier between the pressure, temperature, and humidity sensors and would effectively isolate them from the ambient environment. The RH sensor for example is designed to measure water vapor molecules attaching and detaching from the sensor. The conformal coating on the senor board is specifically designed to prevent that process from happening, thus these two do not work together. Coatings on a temperature sensor can reduce the connection to the ambient environment and slow down the response to changes. And depending on the thickness and uniformity of the coating it could completely seal the pressure sensor. There is no supporting information in the manuscript as to what effect this has on the performance of the sensor. Can the authors comment on the changes in response to the probe this conformal coating has? Are there tests that were done to determine the accuracy/responsiveness of the probe that were completed before and after the conformal coating was applied to showcase the effect the coating has, or prove that it has none?
- There is no presented documentation of any testing done to evaluate the performance of the probe. The first data from the probe shown is in flight during the actual deployment. Given that this is an entirely new system, detailed testing must be done prior to use to ensure that the design is functional and accurate for the intended purposes. Figure 12 and some text around lines 280 suggest that experiments were done to quantify the response of the sensor, but the data from those experiments is not shown in this manuscript nor is information provided regarding the response time of the system (this does not mean the response time of the sensor listed in Table 1, but rather the complete “as deployed” system) or any description of the outcome of those tests if they were completed. This is a significant omission as the sensor package must first be proven reliable before experimental data can be trusted. Additionally, this discussion should be in Section 2 when introducing the details of the probe and not in Section 3 during the case study.
The authors should add a section on the testing done on the original sensor (not the modified one discussed at various points) along with supporting data to demonstrate the performance of the system. What is the response time of the actual system, with the conformal coating and placed inside the nose cone? How does this response time vary with aspiration rate over the external nose cone to simulate the expected fall speed? How were experiments set up to determine the responsiveness of the probe? What are the limitations of the probe design and where is it likely to experience problems? How does this probe compare to currently available instruments like a radiosonde or even surface-based sensors during general conditions and during rapidly changing environments? What tests were done to ensure that the probe was able to accurately observe conditions over the expected range of values for pressure, temperature, and relative humidity?
- From the discussion it appears that the probe collects data from inside the nose cone after separating from the rocket, with a parachute to allow the pseudo-lagrangian behavior, and a few small holes in the nose cone to presumably allow airflow into the nose cone. Furthermore the probe is housed in the nose cone with “expanded polystyrene foam for thermal protection” (line 148) surrounding it. The combination of these factors would lead to a very isolated, poorly mixed connection to the ambient environment with little to no flow over the sensors, effectively disconnecting it from the ambient environment (this is clearly evident in figure 13, more on this in major comment 7). It is also unclear from the manuscript in what orientation the probe collects data in (see major comment 4). Is the nose cone vertical or upside down during data collection? What testing was done with the probe inside the nose cone and outside to show any differences in the responsiveness to changes in the environment? What assumptions are being made regarding the “fall” velocity of the nose cone once the parachute is deployed? What direction is airflow in theory supposed to be entering the nose cone and where does it exit? Were there any tests or calculations performed to determine the flow rate inside the nose cone near where the sensors are located? Were there tests done on the addition of the polystyrene foam to determine what effect this has on the responsiveness of the probe? What design iterations were considered here as alternatives to this design (eg. what is the history of trials that lead to this)?
- Given that the probe is located inside the nose cone, with the pressure sensor mounted to the circuit board itself, there are potential local pressure perturbations due to the design that can negatively affect pressure observations. As air flows over and through objects, Bernoulli effects can lead to potentially significant pressure perturbations depending on flow rates over the objects. It is for this reason that pressure observations at the surface are taken using static pressure ports. Are there tests done that show pressure observations both in and out of the nose cone at varying speeds over an expected range to document any errors the nose cone may be imparting on the observations? There are relatively simple tests that could be performed to document this.
- As it stands currently, I have serious concerns about the validity of any data collected by the probe, especially without documentation. Given these concerns, my recommendation is for the authors to entirely remove any discussion and presentation of data from the thermodynamics of the probe (RH isn’t discussed currently, only temperature and pressure). The kinematic data is novel and worthy of publication but I am not confident in the ability of the probe to accurately represent the thermodynamic environment. If the authors wish to keep the discussion of temperature in the manuscript, then significant additions must be made to the manuscript in order to justify and prove its usefulness, with the above questions addressed in the section.
4). It is unclear from figure 2 how the sensor board actually flies during data collection. The separation charge after burnout from the rocket motors separates the nose cone (which contains the sensor board) from the body, but is the parachute directly tied to the sensor board alone (I think this is true but it’s unclear). More details are needed as to the actual mechanism of deployment for the sensor board, and could benefit from an additional figure or diagram depicting the separation of the sensor board from the rocket body/nose cone. The orientation of the system during data collection is critically important to evaluating the data it has collected.
5). The authors make the point that the probe design is in part to obtain observations without the need to directly enter the circulation (Lines 10-11). I think this is an important point and presents an opportunity for a discussion on deployment/operational safety. I would strongly encourage the authors to add a section at the end of Section 2 (could call it 2.5 Deployment Safety) where safety considerations and a planned deployment strategy are laid out. This would hopefully discourage others from attempting to recklessly or thoughtlessly recreate these observations and would demonstrate the authors commitments to maintaining safety. It’s a good conversation to have, and this is a good opportunity to have it.
6). Lines 250-254, in this paragraph it is unclear whether data in the plots and associated discussion is being presented during the rocket flight and before the probe separation. If the plots are showing data only AFTER the separation, then a note to this effect should be placed in the text. If the plots include data during the rocket phase, this should be clearly indicated in the text and on the plots. The supplementary data showing the video animation of the trajectory appears to indicate the rocket path (in red) before the deployed parachute phase. Given the relatively short rocket phase it is my assumption that this discussion and figure show only deployed data, but it should be made more clear.
7). In connection with major comment 3, Figure 13 shows temperature data from the time of launch (or separation from the rocket, this detail is unclear) from the probe in comparison with data from the 00Z Topeka sounding.
- As a first point, comparing these two soundings is problematic as the probe was launched into convection and the Topeka sounding presumably was not, and was nearly 50 mi away. These environments are not the same and forcing the probe to match the Topeka sounding as what is being shown in Figure 13 completely removes the point of launching the probe into the tornado in the first place. This is effectively forcing the rocket probe to match the Topeka sounding, in which case why not just look at the Topeka sounding?
- A larger issue with this figure is that the sensor probe (pre-correction) is clearly disconnected from the ambient environment. The entire flight shows a temperature range from roughly 35 C to only as low as -10 C despite reaching altitudes as high as 11km, and follows an extremely smooth decay response. Meanwhile the Topeka sounding shows a general environmental change from roughly 20 C to almost -60 C. (again taking into consideration that these are not in the same environment) Assuming the data points are matched by altitude in this figure, at its highest point in altitude the probe indicates a temperature of +15 C while the Topeka sounding indicates the temperature should have been closer to -80 C. The general look of the temperature trace is a clear indication that the probe is almost completely isolated from the ambient environment and has an excessively long response time (likely due to the factors I list in comment 3), thereby making the temperature observations unusable. Can the authors comment here on why they think the data are scientifically valid given the excessively large disparity between the probe temperature and a generic environmental profile in the region?
- It is curious how the “corrected” data have a significant amount more variability than the original uncorrected data. Generally, corrections tend to work the opposite way and smooth the data further. This raises questions and concerns about the accuracy of the correction that was applied as it appears to be unstable and variable, changing from point to point. Additionally, the logic behind the flow rate being near zero due to the sensor being pseudo-lagrangian is flawed. Given that the sensor/nose cone has a mass, it has a fall speed in all Even in updrafts, the probe would still be “falling” relative to the environment around it, even if it’s ground relative velocity is positive. The velocity inside the nose cone where the probe is however is probably zero or near zero given the behavior of the temperature response. Can the authors expand on their correction factor, explaining how the corrected data has significantly more variation than the original data? Can the authors comment on the applicability of a correction factor that results in a nearly 80 C swing in temperature? Can the authors comment on using the Topeka sounding to force the data to a specific profile rather than determining the correction factor organically off known and controlled test data?
- “Corrections” are not meant to modify the data to this extent and are not appropriate in this context. Given the apparent behavior of the sensor in regards to temperature, I suggest removing the thermodynamic observations from the manuscript entirely, unless the authors can demonstrate that the probe is capable of collecting accurate and representative observations through rigorous ground tests.
Minor comments:
Line 4: Suggest adding “horizontal” before “….velocity of 85.1 ms-1…” to clarify direction of motion
Line 4-5: The current statement indicates a measured pressure deficit of -113.5 hPa at an altitude of 475 m. Is this pressure deficit relative to the ambient pressure at that altitude or relative to the surface pressure? If it’s surface pressure, is this taking into account the vertical decrease in pressure due to altitude (standard atmosphere is roughly 1 hPa per 10 m, which would mean 47.5 hPa of that change is just due to altitude, and there are questions whether a standard atmosphere applies in this context)? If it’s relative to the ambient pressure outside the tornado vortex how is that ambient pressure obtained? Clarification of the context is needed here. A simple statement of the context is sufficient here, with further expansion in the body of the text.
Line 6: please specify whether this velocity is vertical or horizontal
Line 8: was the probe tracked all the way to the surface or was the transmitted data cutoff at some altitude?
Line 13: Suggest “Supercell tornadoes are among the most damaging...”
Line 20: Suggest adding “…and the relative danger posed in this region.” at the end of this line. Probably good to highlight the danger of this environment and a focus on safety.
Line 23: Suggest adding “….capable of causing intense, localized damage.”
Line 23-24: Are there references for the mentioned high-resolution cameras and drone videos? Even if they’re social media posts I think it’s worth citing the work.
Line 24: Suggest modifying the end of this paragraph to the following: “…documented these damaging updrafts of tornadoes in recent years, but direct observations are essential to determine the conditions responsible for the structural damage and human impact. However these observations are rare and relatively limited.” Then remove the similar themed sentence on lines 36-37.
Line 33: Suggest combining this paragraph, following the above suggestion, with the previous paragraph as they are both detailing surface observations in tornadoes.
Line 45: Suggest moving this statement to the end of the introduction section in a new transition paragraph, see major comment 1.
Line 47: Three decades (VORTEX was in the 90’s), and “Project” is not needed here.
Line 53: This does not need to be a separate paragraph. Nor does the paragraph beginning on Line 57. Combine these as they all talk about radar analysis efforts.
Line 55: I would reword to “The UAS technology deployed in the TORUS project is not ….” And move this sentence to the end of the “radar” paragraph.
Line 80: Suggest “To address the needed observations, the authors designed….”
Line 135: This would be a good place to move the “previous attempts” information/discussion.
Line 159: combine this paragraph with the previous, start sentence with: “These regulations specify that a Class 1…”, and move reference to FAA at the end of the sentence.
Line 162-167: these statements can be combined into a single paragraph, consider reducing text for redundancy (the “"in a cleared area, free of tall trees, power lines, buildings, and dry brush and grass” is repeated)
Line 170: I would also add that the weight and density of the payload and rocket is comparable to a radiosonde to further strengthen your case that the rocket and payload pose minimal threat.
Line 191: Suggest adding “Throughout the day a dryline would…”
Line 195: “NOAA’s Storm Prediction Center upgraded….”
Line 210-212: “Previous experience has demonstrated that a narrow zone of inflow into the northeast quadrant of a tornado is often free of destructive hail which would damage the rocket (Fig. 8).”
Line 216: “At 23:17:33 UTC the rocket was launched and the payload was deployed.”
Figure 9: I would add that the GPS track is from the retrieved 10 Hz data to the figure caption. (Assuming that’s a correct statement)
Line 230: It’s not strictly fair to say that the GPS directly measures the wind, it’s inferred based on the motion. Suggest rewording sentence to “The GPS velocity data recorded by the probe resolves the in situ wind speeds during the 30.2-minute flight inside the tornado and parent mesocyclone with the assumption that the pseudo-Lagrangian drifter follows the flow with minimal probe-induced motion following the parachute deployment phase.”
Line 234: I think it would be helpful here to add a note about the duration of time between launch and the apex of the trajectory to provide a sense for how much the storm may have moved during the flight path. This is indicated in Figure 10 to an extent, but reiterating it here would be helpful.
Line 238: I would also add the maximum horizontal component (looks to be in the 70 ms-1 ballpark) to this statement, as well as indicate the altitude at which these occur. This would add a bit of context to the data points.
Figure 10: What are the vertical dotted lines on the plots?
Figure 11: This is a good figure, I just suggest making the axis labels slightly larger and bolded to make them more visible.
Line 257: It’s not uncommon for sensors to work outside of their typical operating ranges, however comparing the pressure data collected here to pressure data from a NWS radiosonde flight that was 40 mi away and not in the sampled storm may present differences in pressure at a specific altitude. Can the authors comment here on the assumptions (and the validity of those assumptions) inherent in this comparison?
Line 285: how is the ambient external temperature known at a point during the descent at the location of the probe?
Line 290: This statement cannot be true as the probe will always have a descent speed given that it is not “freely floating” in the atmosphere. Earlier in the manuscript the authors estimated the ambient fall speed with the parachute deployed to be in the 4-6 m s-1 range, that assumption should carry here.
Figure 13: Need axis labels for the plot
Lines 310-320: There are several statements here about design changes made for future deployments. While these are important, they belong in the conclusions section not in the discussion of the current data which did not have these changes. The manuscript is presenting data collected by the original sensor (at least without the modifications) and the discussion of the data should be kept in the confines of that sensor.
Line 320: more of a comment than anything, the authors are justified in neglecting solar radiation in this context. Not only is there minimal solar heating effects as the sensor is in cloud, the probe design has the sensor inside the nose cone, shielding it entirely from any solar radiation effects. While the move to a gold and black sensor on the next iteration (again, move to conclusions under future work) will help with this as they are external, the sensors would still need to be calibrated against potential solar heating effects.
Citation: https://doi.org/10.5194/egusphere-2023-781-RC2
Reed Timmer et al.
Data sets
Data Received By The Probe Reed Timmer, Mark Simpson, Sean Schofer, Curtis Brooks https://www.doi.org/10.17605/OSF.IO/Z64FD
Video supplement
A video animation of the probe trajectory (Supplemental1.mov) and a video recording of the rocket launch (Supplemental2.mov) Reed Timmer, Mark Simpson, Sean Schofer, Curtis Brooks https://www.doi.org/10.17605/OSF.IO/UBTN5
Reed Timmer et al.
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