Capillary Flow Experiment (CFE) is a suite of fluid physics experiments that investigate capillary flows and flows of fluids in containers with complex geometries. Results will improve current computer models that are used by designers of low gravity fluid systems and may improve fluid transfer systems on future spacecraft.Principal Investigator(s)
ZIN Technologies Incorporated, Cleveland, OH, United States
National Center for Microgravity Research, Cleveland, OH, United States
National Aeronautics and Space Administration (NASA)Sponsoring Organization
Human Exploration and Operations Mission Directorate (HEOMD)Research Benefits
Information PendingISS Expedition Duration:
April 2004 - April 2008Expeditions Assigned
9,12,13,14,15,16Previous ISS Missions
Similar experiments were performed on Mir as well as ISS Expeditions 9, 12, 13, 14 and 15.
The Capillary Flow Experiment (CFEs) is a suite of fluid physics experiments whose purpose is to investigate capillary flows and phenomena in low gravity. The CFE data to be obtained will be crucial to future space exploration because they provide a foundation for physical models of fluids management in microgravity, including fuel tanks and cryogen storage systems, Thermal Control Systems (TCS) (e.g., water recycling), and materials processing in the liquid state. NASA's current plans for Exploration missions assume the use of larger liquid propellant masses than have ever flown before. Under low-gravity conditions, capillary forces can be exploited to control fluid orientation so that such large mission-critical systems perform predictably.
The handheld experiments common to the suite aim to provide results of critical interest to the capillary flow community that cannot be achieved in ground-based tests; for example, dynamic effects associated with a moving contact boundary condition, capillary-driven flow in interior corner networks, and critical wetting phenomena in complex geometries. Specific applications of the results center on particular fluids challenges concerning propellant tanks. The knowledge gained will help spacecraft fluid systems designers increase system reliability, decrease system mass, and reduce overall system complexity.
CFE encompasses three experiments, CFE-Contact Line (CFE-CL), CFE-Interior Corner Flow (CFE-ICF), and CFE Vane Gap (CFE-VG), with two unique experimental apparatuses per experiment. There are multiple tests per experiment. Each of the experiments employs conditions and test cell dimensions that cannot be achieved in ground-based experiments. All of the units use similar fluid injection hardware made of Lucite, have simple and similarly sized test chambers, and rely solely on video for highly quantitative data. Silicone oil is used as the fluid. Differences between units are primarily fluid properties, wetting conditions (determined by the coating inside the test chamber), and test cell cross section.
The knowledge gained from this payload has the potential to be instrumental in the design of future fluid systems for spacecraft-impacting fluid bearing containers such as propellant and cryogenic fluids tanks, thermal control system coolant reservoirs, water storage and management systems, liquid state low-gravity materials processing equipment, and biofluids handling instruments for inflight human health systems. By performing this experiment, researchers will gain information that will lead to improvements in system reliability with reductions in system mass and complexity. These applications of CFE are in direct support of NASA's mission to develop safe, reliable, and affordable spacecraft to pursue the greater exploration of our solar system and universe.Earth Applications
The results of the flight experiments are also expected to provide insights into terrestrial interfacial phenomena and may lead to models predicting fluid flows in porous media (i.e. ground water transport), complex capillary structures (i.e. high performance wicks for heat pipes employed in electronics cooling), and Lab-On-Chip technologies (i.e., microscale biofluids processing).
During the CL experiments, crewmembers will allow the fluids to settle out for approximately 20 min. The crew will then impart disturbances by tapping, pushing, sliding, swirling, and shaking the CFE unit. The crew will start and stop the camcorder and change/label tapes as required to record all tests. Following each disturbance, the crew will allow the fluids to dampen before proceeding to the next disturbance.
For the VG sessions, crewmember will fills the test chamber with fluid and then record the background g-jitter during an undisturbed wait with the ISS camcorder. For VG-2, crewmembers will then increment the vane through one complete revolution capturing the advance and recession of the fluid along each side of the vane. The critical angles at which the fluid spontaneously rises to the top of each side the vane are also determined and recorded. This test is special in that the surface is dry and is not repeatable. During VG-1, crewmembers will increment the vane through two complete revolutions capturing the advance and recession of the fluid along each side of the vane. The critical angles at which the fluid spontaneously rises to the top of each side the vane are also determined and recorded. This test sees a wet surface in the test chamber and vane and may be repeated as many times as necessary.
For the ICF experiments, the crewmember injects a fluid from a self-contained reservoir into the test chamber and primes the tube between valve 2 and the test chamber vertex. The crewmember will then turn the knob and open/close valves 1 or 2 to dispense or retract fluid into test chamber. Fluid creeps from test chamber base to top vertex and is then recovered to a reservoir.
The crew will set up the Maintenance Work Area (MWA) work surface and camcorder, attach the CFE units onto the MWA, inject the fluids into the test chambers, and record the fluid's response to disturbances using the ISS camcorder.
CFE is a suite of fluid physics experiments whose purpose is to investigate capillary flows and phenomena in low gravity and consists of three investigations: Interior Corner Flow (ICF), Vane Gap (VG) and Contact Line (CL). The results summarized here encompass the CFE experiments carried out onboard the International Space Station (ISS) beginning during Increment 9 (August 2004) and continuing through Increment 16 (December 2007). The results from these experiments will be used to develop more accurate fluid models to aide in the design of low gravity fluid systems and enhance the fluid transfer systems of future space vehicles (Weislogel 2008).
Interior Corner Flow (ICF)
CFE-ICF studies capillary flows in interior corners of two tapered containers. The ullage (empty part of the container) migration rates of four different flows (dry, wet, open loop and bubbly) in the units were observed and compared. Migration rates were found to be in surprising agreement with predictions for the dry tests, but were under-predicted for previously wetted surfaces.. In the case of ICF-2, the migration rate also increased for the bubbly flow test. For ICF-1, bubbly flows were created, but have not been analysed to date. This analysis is ongoing and will be completed in part with further experimental results to be collected during CFE-2 experiments currently onboard ISS. In many cases the bubbles were separated during the bubble tests of ICF but small bubbles were unhindered (Weislogel 2008).
Vane Gap (VG)
The Capillary Flow Experiment-Vane Gap (CFE-VG) studies capillary flow when there is a gap between interior corners, such as in the gap formed by an interior vane and tank wall of a large propellant storage tank or the near intersection of vanes in a tank with a complex vane network.
In the case of the perfectly wetting fluid of VG-1, three wetting configurations were produced: wetting along the small gap between the vane and cylinder, wetting along the large gap and a large shift in fluid from one side of the container to the other (bulk shift). The most noteworthy condition was the bulk shift due to the considerable amount of liquid that was transferred. The average observed large and small gap critical wetting angles (vane angles at which fluid draws up the gap formed between the vane and cylinder wall and “wets” the entire length of the vane) were in close agreement with analytical predictions. However, bulk shift was not predicted by analysis, which assumed perfect geometric symmetry of vane and cylinder. The occurrence of bulk shift indicates that small irregularities in geometry (such as tiny imperfections within the manufacturing tolerance of the experiment unit) can influence fluid behavior in a significant way (Chen 2008). Post flight measurements of test cell asymmetries were made to quantify such values and new predictions were made of the slightly asymmetric vessel. The agreement is informative as a method to assess tank symmetry for applications aboard spacecraft.
For the partial wetting fluid of VG-2, wetting occurred along both the small and large gaps, similar to VG-1. However, unlike VG-1, the difference between the average observed and average predicted critical wetting angles was substantial, and could be due to asymmetry inherent in the experiment unit and contact angle hysteresis (the difference between the receding (uphill) angle and advancing (downhill) angle made by the fluid on a tilted plane right before the fluid drop begins to roll). Bulk shift of the fluid was not predicted and did not occur, or was not observed in previous studies (Chen 2008).
Contact Line (CL)
CFE-CL investigates the properties of the contact line (the boundary between the liquid and the solid surface of the container), which controls the interface shape, stability, and dynamics of capillary systems in low gravity. From the over 400 events evaluated thus far, damping rate, frequency and qualitative waveform were found to be plainly influenced by contact line and contact angle conditions. The pinning condition produced higher frequencies and lower damping rates than the smooth condition. Larger contact angles also produced the same trend in higher frequencies and lower damping rates. Fluid depth was found to have little effect on the fluid response to disturbances except in cases where shallow tests were performed intentionally (Weislogel 2008).
Observed results were also compared to model predictions. Agreement between numerical predictions and observed results varied widely. The most accurately modeled instance was the perfectly wetting case of CL-2 for both the pinning and smooth conditions and for both axial and lateral disturbance events. The least accurately modeled instances were the high contact angle push-type disturbance events with free-slip conditions, since contact line translation is not included in the constant contact angle slip model. In general, modeled and observed results were in best agreement for pinned conditions, as a result of the more predictable and confined contact line movement (Weislogel 2008).
A database comprising videos and datasheets containing experiment parameters, data and preliminary results of all CL events is being compiled by the investigators to facilitate further investigation and model refinement (Weislogel 2008).
Weislogel MM, Chen Y, Bolleddula DA. A better nondimensionalization scheme for slender laminar flows: The Laplacian operator scaling method. Physics of Fluids. 2008; 20(9): 093602-1 -093602-7. DOI: 10.1063/1.2973900.
Chen Y, Jenson RM, Weislogel MM, Collicott SH. Capillary Wetting Analysis of the CFE-Vane Gap Geometry. 46th Aerospace Sciences Meeting and Exhibit, Reno, NV; 2008
Klatte J, Haake D, Weislogel MM, Dreyer M. A fast numerical procedure for steady capillary flow in open channels. Acta Mechanica. 2008; ;201:269-276.: 269-276. DOI: 10.1007/s00707-008-0063-1.
Jenson RM, Weislogel MM, Klatte J, Dreyer M. Dynamic Fluid Interface Experiments Aboard the International Space Station: Model Benchmarking Dataset. Journal of Spacecraft and Rockets. 2010 July-August; 47(4): 670-679. DOI: 10.2514/1.47343.
Weislogel MM, Jenson RM, Collicott SH, Williams SL. Geometry Pumping on Spacecraft (The CFE-Vane Gap Experiments on ISS). Japan Society of Microgravity Application. 2008; 25(3): 291-295.
Weislogel MM, Jenson RM, Chen Y, Collicott SH, Klatte J, Dreyer M. The capillary flow experiment aboard the International Space Station: Status. Acta Astronautica. 2009; ;65:861-869.: 861-869. DOI: 10.1016/j.actaastro.2009.03.008.
Jenson RM, Weislogel MM, Tavan NT, Bunnell CT. Capillary Flow Experiments Aboard ISS. 47th Aerospace Sciences Meeting and Exhibit, Orlando, FL; 2009
Weislogel MM, Bunnell CT, Kurta CE, Golliher EL, Green RD, Hickman JM. Preliminary Results from the Capillary Flow Experiment Aboard ISS: The Moving Contact Line Boundary Condition. 43rd Aerospace Sciences Meeting and Exhibit, Reno, NV; 2005
Weislogel MM, Jenson RM, Dreyer M, Klatte J. Interim Results from the Capillary Flow Experiment Aboard ISS: the Moving Contact Line Boundary Condition. 45th Aerospace Sciences Meeting and Exhibit, Reno, NV; 2007
Weislogel MM, Jenson RM, Klatte J, Dreyer M. The Capillary Flow Experiments aboard ISS: Moving Contact Line Experiments and Numerical Analysis. 46th Aerospace Sciences Meeting and Exhibit, Reno, NV; 2008
Weislogel MM, Jenson RM, Chen Y, Collicott SH, Klatte J, Dreyer M. Postflight summary of the Capillary Flow Experiments aboard the International Space Station. 59th International Astronautical Congress, Glasgow, Scotland; 2008
Weislogel MM, Jenson RM, Chen Y, Collicott SH, Klatte J, Dreyer M. The capillary flow experiments aboard the International Space Station: Status. Acta Astronautica. 2009 September; 65(5-6): 861-869. DOI: 10.1016/j.actaastro.2009.03.008.
Thomas CM, Ma Y, North A, Weislogel MM. Microgravity condensing heat exchanger. United States Patent and Trademark Office.7,913,499. Jul 1 2008.
Weislogel MM, Thomas EA, Graf J. Systems and methods for separating a multiphase fluid. United States Patent and Trademark Office.7,905,946. Aug 12 2008.
Concus P, Finn R, Weislogel MM. Measurement of Critical Contact Angle in a Microgravity Experiment. Experiments in Fluids. 2000; 28: 197-205.
Weislogel MM, Nardin CL. Passive Fluids Management in Low-g: Partially Wetting Systems. 42nd Aerospace Sciences Meeting and Exhibit, Reno, NV; 2004 2004-1152.
Chen Y, Weislogel MM, Bolleddula DA. Capillary Flow in Cylindrical Containers with Rounded Interior Corners. 45th Aerospace Sciences Meeting and Exhibit, Reno, NV; 2007 AIAA-2007-745.
Concus P, Finn R, Weislogel MM. Capillary Surfaces in an Exotic Container: Results from Space Experiments. Journal of Fluid Mechanics. 1999; 394: 119-135.
Weislogel MM, Collicott SH, Gotti DJ, Bunnell CT, Kurta CE, Golliher EL. The Capillary Flow Experiments: Handheld Fluids Experiments for International Space Station. 42nd Aerospace Sciences Meeting and Exhibit, Reno, NV; 2004 2004-1148.
Weislogel MM, Jenson RM, Bolleddula DA. Capillary Driven Flows in Weakly 3-Dimensional Polygonal Containers. 45th Aerospace Sciences Meeting and Exhibit, Reno, NV; 2007 AIAA-2007-748.
Chen Y, Weislogel MM. Analysis of Capillary Flow in Rounded Corners. Heat Transfer and Fluids Engineering Summer Conference, Charlotte, NC; 2004 HT-FED2004-56253.