INVESTIGATION OF SUBSTRUCTURE HEATING ON CRACKED ABLATIVE HEAT SHIELDS
An experimental program was carried out to study the effect of cracks in an ablative heat shield on the substructure heating. The test conditions involved stagnation pressures of 20 to 30 atmospheres, temperatures of 4000 to 9000R, and Mach numbers of 2.3 and 3. The models, made of teflon, has trans...
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| creator | Winkler,Eva M Humphrey,Richard L Koenig,Joseph A Madden,Michael T |
| description | An experimental program was carried out to study the effect of cracks in an ablative heat shield on the substructure heating. The test conditions involved stagnation pressures of 20 to 30 atmospheres, temperatures of 4000 to 9000R, and Mach numbers of 2.3 and 3. The models, made of teflon, has transverse and longitudinal cracks machined into the surface. They were instrumented for pressure, temperature, heat transfer and skin-friction measurements. The cracks were found to have pronounced effects on the ablative behavior. The heating is moderate under a laminar boundary layer, but can be catastrophic when the boundary layer is turbulent, depending upon the size and direction of the crack. The results for the transverse cracks were compared with an available analytical prediction. Ablation was found to reduce the wall shear stress by 40 percent or more. (Author) |
| format | Report |
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The test conditions involved stagnation pressures of 20 to 30 atmospheres, temperatures of 4000 to 9000R, and Mach numbers of 2.3 and 3. The models, made of teflon, has transverse and longitudinal cracks machined into the surface. They were instrumented for pressure, temperature, heat transfer and skin-friction measurements. The cracks were found to have pronounced effects on the ablative behavior. The heating is moderate under a laminar boundary layer, but can be catastrophic when the boundary layer is turbulent, depending upon the size and direction of the crack. The results for the transverse cracks were compared with an available analytical prediction. Ablation was found to reduce the wall shear stress by 40 percent or more. (Author)</description><language>eng</language><subject>ABLATION ; AERODYNAMIC HEATING ; Aerodynamics ; CRACKS ; Fluid Mechanics ; Guided Missile Reentry Vehicles ; HALOCARBON PLASTICS ; HEAT SHIELDS ; HEAT TRANSFER ; LAMINAR BOUNDARY LAYER ; PRESSURE ; REENTRY VEHICLES ; SHEAR STRESSES ; SKIN FRICTION ; STAGNATION POINT ; SUPERSONIC CHARACTERISTICS ; TURBULENT BOUNDARY LAYER</subject><creationdate>1969</creationdate><rights>APPROVED FOR PUBLIC RELEASE</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27566,27567</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0699136$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Winkler,Eva M</creatorcontrib><creatorcontrib>Humphrey,Richard L</creatorcontrib><creatorcontrib>Koenig,Joseph A</creatorcontrib><creatorcontrib>Madden,Michael T</creatorcontrib><creatorcontrib>NAVAL ORDNANCE LAB WHITE OAK MD</creatorcontrib><title>INVESTIGATION OF SUBSTRUCTURE HEATING ON CRACKED ABLATIVE HEAT SHIELDS</title><description>An experimental program was carried out to study the effect of cracks in an ablative heat shield on the substructure heating. The test conditions involved stagnation pressures of 20 to 30 atmospheres, temperatures of 4000 to 9000R, and Mach numbers of 2.3 and 3. The models, made of teflon, has transverse and longitudinal cracks machined into the surface. They were instrumented for pressure, temperature, heat transfer and skin-friction measurements. The cracks were found to have pronounced effects on the ablative behavior. The heating is moderate under a laminar boundary layer, but can be catastrophic when the boundary layer is turbulent, depending upon the size and direction of the crack. The results for the transverse cracks were compared with an available analytical prediction. Ablation was found to reduce the wall shear stress by 40 percent or more. (Author)</description><subject>ABLATION</subject><subject>AERODYNAMIC HEATING</subject><subject>Aerodynamics</subject><subject>CRACKS</subject><subject>Fluid Mechanics</subject><subject>Guided Missile Reentry Vehicles</subject><subject>HALOCARBON PLASTICS</subject><subject>HEAT SHIELDS</subject><subject>HEAT TRANSFER</subject><subject>LAMINAR BOUNDARY LAYER</subject><subject>PRESSURE</subject><subject>REENTRY VEHICLES</subject><subject>SHEAR STRESSES</subject><subject>SKIN FRICTION</subject><subject>STAGNATION POINT</subject><subject>SUPERSONIC CHARACTERISTICS</subject><subject>TURBULENT BOUNDARY LAYER</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1969</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZHDz9AtzDQ7xdHcM8fT3U_B3UwgOdQoOCQp1DgkNclXwcAWK-7krAKWcgxydvV1dFBydfIBiYRA5hWAPT1cfl2AeBta0xJziVF4ozc0g4-Ya4uyhm1KSmRxfXJKZl1oS7-hiYGZpaWhsZkxAGgANtSl_</recordid><startdate>19690722</startdate><enddate>19690722</enddate><creator>Winkler,Eva M</creator><creator>Humphrey,Richard L</creator><creator>Koenig,Joseph A</creator><creator>Madden,Michael T</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>19690722</creationdate><title>INVESTIGATION OF SUBSTRUCTURE HEATING ON CRACKED ABLATIVE HEAT SHIELDS</title><author>Winkler,Eva M ; Humphrey,Richard L ; Koenig,Joseph A ; Madden,Michael T</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD06991363</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1969</creationdate><topic>ABLATION</topic><topic>AERODYNAMIC HEATING</topic><topic>Aerodynamics</topic><topic>CRACKS</topic><topic>Fluid Mechanics</topic><topic>Guided Missile Reentry Vehicles</topic><topic>HALOCARBON PLASTICS</topic><topic>HEAT SHIELDS</topic><topic>HEAT TRANSFER</topic><topic>LAMINAR BOUNDARY LAYER</topic><topic>PRESSURE</topic><topic>REENTRY VEHICLES</topic><topic>SHEAR STRESSES</topic><topic>SKIN FRICTION</topic><topic>STAGNATION POINT</topic><topic>SUPERSONIC CHARACTERISTICS</topic><topic>TURBULENT BOUNDARY LAYER</topic><toplevel>online_resources</toplevel><creatorcontrib>Winkler,Eva M</creatorcontrib><creatorcontrib>Humphrey,Richard L</creatorcontrib><creatorcontrib>Koenig,Joseph A</creatorcontrib><creatorcontrib>Madden,Michael T</creatorcontrib><creatorcontrib>NAVAL ORDNANCE LAB WHITE OAK MD</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Winkler,Eva M</au><au>Humphrey,Richard L</au><au>Koenig,Joseph A</au><au>Madden,Michael T</au><aucorp>NAVAL ORDNANCE LAB WHITE OAK MD</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>INVESTIGATION OF SUBSTRUCTURE HEATING ON CRACKED ABLATIVE HEAT SHIELDS</btitle><date>1969-07-22</date><risdate>1969</risdate><abstract>An experimental program was carried out to study the effect of cracks in an ablative heat shield on the substructure heating. 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| subjects | ABLATION AERODYNAMIC HEATING Aerodynamics CRACKS Fluid Mechanics Guided Missile Reentry Vehicles HALOCARBON PLASTICS HEAT SHIELDS HEAT TRANSFER LAMINAR BOUNDARY LAYER PRESSURE REENTRY VEHICLES SHEAR STRESSES SKIN FRICTION STAGNATION POINT SUPERSONIC CHARACTERISTICS TURBULENT BOUNDARY LAYER |
| title | INVESTIGATION OF SUBSTRUCTURE HEATING ON CRACKED ABLATIVE HEAT SHIELDS |
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