{"project":{"acronym":"","projectId":9399,"title":"High Frequency Measurements in Shock-Wave/Turbulent Boundary-Layer Interaction at Duplicated Flight Conditions","primaryTaxonomyNodes":[{"taxonomyNodeId":10931,"taxonomyRootId":8816,"parentNodeId":10929,"level":3,"code":"TX14.2.2","title":"Heat Transport","definition":"Heat transport enables moving waste energy from a vehicle component and/or system for either rejection to the environment or re-use elsewhere within the vehicle. This area includes technologies for both spacecraft and electrified aircraft propulsion thermal management. The transport of energy is accomplished using active and/or passive capabilities within a thermal control system. Technologies include those items that can more effectively transfer heat, as well as methods to advance robustness, life, efficiency, and temperature range of operability.","exampleTechnologies":"Heat pipes (e.g. constant conductance, variable conductance, diode), capillary pumped fluid loops, loop heat pipes, mechanically pumped fluid loops (e.g., single phase and two phase), thermal straps, forced air cooling (heating, ventilation, and air conditioning (HVAC)), fans, heat pumps (e.g., thermoelectric coolers, vapor compression systems), vapor cooling, heat switches (e.g. paraffin, coefficient of thermal expansion, shape memory alloys), solid state conduction bars/doublers (e.g. high thermal conductivity composites), loop heat pipe and high heat load transport (500 kW - 1 MW), two phase heat transport and pool boiling","hasChildren":false,"hasInteriorContent":true}],"startTrl":4,"currentTrl":7,"endTrl":7,"benefits":"In aeronautics, heat flux sensors will help meet measurement challenges in providing validation and verification of CFD codes for heat transfer. Development of reliable turbulence modeling and CFD codes depend on making precise aerothermodynamic measurements of heat flux on various test models. NASA ARMD specifically cites prediction of transition and flow separation as high-priority objectives for the future of aeronautics, and heat transfer measurements is a key tool in providing insight into the dynamics of flow phenomena in SWTBLI regions. Specific applications of interest include SWTBLI at high enthalpies (flap forces and Scramjet), laminar/turbulent transition (crossflow instability), and unsteady separated/reattaching backshell flows on capsules.
Apart from the military hypersonic applications, high-sensitivity, high-bandwidth heat transfer instrumentation would be useful for general spatiotemporally accurate measurement of temperature and heat flux. The electronics could be used for measurements in turbomachinery (turbine blades) and for pulse detonation engines. One interesting commercial application where high-temperature heat flux measurement would be useful is fuel cell research, in which spatiotemporal heat flux is critical for performance evaluation. Another application is fire monitoring/control. As an example, it would be useful for naval ships to monitor the heat flux from weapons systems to adjoining areas.","description":"Large amplitude, unsteady heating loads and steep flow gradients produced in regions of shock-wave/turbulent boundary-layer interaction (SWTBLI) pose a serious and challenging problem for designers of hypersonic vehicles. Characterizing SWTBLI flow features, such as the size of flow separation, is important for design evaluation and CFD validation. Tao Systems and CUBRC propose to develop a wide-bandwidth, thin-film heat transfer sensor system that quantifies the high frequency SWTBLI at duplicated flight conditions. This effort combines Tao Systems' high frequency-response/high-sensitivity electronics and signal processing techniques with the unique expertise of CUBRC in high-speed, high-enthalpy flows to obtain spatiotemporal information for the development of physics-based turbulence models.","startYear":2012,"startMonth":4,"endYear":2015,"endMonth":6,"statusDescription":"Completed","principalInvestigators":[{"contactId":33953,"canUserEdit":false,"firstName":"Arun","lastName":"Mangalam","fullName":"Arun Mangalam","fullNameInverted":"Mangalam, Arun","primaryEmail":"arun@taosystems.us","publicEmail":true,"nacontact":false}],"programDirectors":[{"contactId":206378,"canUserEdit":false,"firstName":"Jason","lastName":"Kessler","fullName":"Jason L Kessler","fullNameInverted":"Kessler, Jason L","middleInitial":"L","primaryEmail":"jason.l.kessler@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":215154,"canUserEdit":false,"firstName":"Jennifer","lastName":"Gustetic","fullName":"Jennifer L Gustetic","fullNameInverted":"Gustetic, Jennifer L","middleInitial":"L","primaryEmail":"jennifer.l.gustetic@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":62051,"canUserEdit":false,"firstName":"Carlos","lastName":"Torrez","fullName":"Carlos Torrez","fullNameInverted":"Torrez, Carlos","primaryEmail":"carlos.torrez@nasa.gov","publicEmail":true,"nacontact":false}],"projectManagers":[{"contactId":263567,"canUserEdit":false,"firstName":"Katie","lastName":"Boyles","fullName":"Katie A Boyles","fullNameInverted":"Boyles, Katie A","middleInitial":"A","primaryEmail":"katie.a.boyles@nasa.gov","publicEmail":true,"nacontact":false},{"contactId":461333,"canUserEdit":false,"firstName":"Theresa","lastName":"Stanley","fullName":"Theresa M Stanley","fullNameInverted":"Stanley, Theresa M","middleInitial":"M","primaryEmail":"theresa.m.stanley@nasa.gov","publicEmail":true,"nacontact":false}],"website":"","libraryItems":[{"caption":"High Frequency Measurements in Shock-Wave/Turbulent Boundary-Layer Interaction at Duplicated Flight Conditions Project Image","file":{"fileExtension":"jpg","fileId":298372,"fileName":"SBIR_2010_2_BC_A2.06-8327","fileSize":232187,"objectId":294906,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"226.7 KB"},"files":[{"fileExtension":"jpg","fileId":298372,"fileName":"SBIR_2010_2_BC_A2.06-8327","fileSize":232187,"objectId":294906,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"226.7 KB"}],"id":294906,"title":"Project Image","description":"High Frequency Measurements in Shock-Wave/Turbulent Boundary-Layer Interaction at Duplicated Flight Conditions Project Image","libraryItemTypeId":1095,"projectId":9399,"primary":true,"publishedDateString":"","contentType":{"lkuCodeId":1095,"code":"IMAGE","description":"Image","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}}],"transitions":[{"transitionId":64002,"projectId":9399,"partner":"Other","transitionDate":"2012-04-01","path":"Advanced From","relatedProjectId":9095,"relatedProject":{"acronym":"","projectId":9095,"title":"High Frequency Measurements in Shock-Wave/Turbulent Boundary-Layer Interaction at Duplicated Flight Conditions","startTrl":1,"currentTrl":4,"endTrl":4,"benefits":"Apart from the military hypersonic applications, high-sensitivity, high-bandwidth heat transfer instrumentation would be useful for general spatiotemporally accurate measurement of temperature and heat flux. 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In aeronautics, heat flux sensors will help meet measurement challenges in providing validation and verification of CFD codes for heat transfer. Development of reliable turbulence modeling and CFD codes depend on making precise aerothermodynamic measurements of heat flux on various test models. NASA ARMD specifically cites prediction of transition and flow separation as high-priority objectives for the future of aeronautics, and heat transfer measurements is a key tool in providing insight into the dynamics of flow phenomena in SWTBLI regions. Specific applications of interest include SWTBLI at high enthalpies (flap forces and Scramjet), laminar/turbulent transition (crossflow instability), and unsteady separated/reattaching backshell flows on capsules.","description":"Large amplitude, unsteady heating loads and steep flow gradients produced in regions of shock-wave/turbulent boundary-layer interaction (SWTBLI) pose a serious and challenging problem for designers of hypersonic vehicles. Characterizing SWTBLI flow features, such as the size of flow separation, is important for design evaluation and CFD validation. Tao Systems and CUBRC propose to develop a wide-bandwidth, thin-film heat transfer sensor system that quantifies the high frequency SWTBLI at duplicated flight conditions. This effort combines Tao Systems' high frequency-response/high-sensitivity electronics and signal processing techniques with the unique expertise of CUBRC in high-speed, high-enthalpy flows to obtain spatiotemporal information for the development of physics-based turbulence models.","startYear":2011,"startMonth":2,"endYear":2011,"endMonth":9,"statusDescription":"Completed","website":"","program":{"acronym":"SBIR/STTR","active":true,"description":"
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The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
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The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
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