APPROXIMATE CALCULATION ON NON-STEADY-STATE FUSION OF VITREOUS MATERIALS (PRIBLIZHENNYI RASCHET NESTATSIONARNOGO OPLAVLENIYA STEKLOVIDNYKH MATERIALOV)
The problem of unsteady ablation of glassy materials subjected to aerodynamic heating is considered. An approximate integral method is outlined for calculating the significant ablation parameters. The method is applied to determining heat transfer rates and surface temperature at the stagnation poin...
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| creator | Matveev,S. K |
| description | The problem of unsteady ablation of glassy materials subjected to aerodynamic heating is considered. An approximate integral method is outlined for calculating the significant ablation parameters. The method is applied to determining heat transfer rates and surface temperature at the stagnation point of a blunted body. The differential equation derived from the equation of conservation of energy is used to calculate the surface temperature of the melted film. A comparison of the numerical results obtained by this method with the exact solution shows satisfactory agreement. It is said that this method may be used when similar solutions are not valid and successfully applied to calculations of unsteady melting of a glass shield not only in the stagnation region, but also on the surface of the body. (Author)
Edited trans. of Inzhenerno-Fizicheskii Zhurnal (USSR) v11 n6 p730-736 1966. |
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Edited trans. of Inzhenerno-Fizicheskii Zhurnal (USSR) v11 n6 p730-736 1966.</description><language>eng</language><subject>ABLATION ; AERODYNAMIC HEATING ; APPROXIMATION(MATHEMATICS) ; ATMOSPHERE ENTRY ; BLUNT BODIES ; CERAMIC COATINGS ; CERAMIC MATERIALS ; DIFFERENTIAL EQUATIONS ; Guided Missiles ; HEAT SHIELDS ; HEAT TRANSFER ; NUMERICAL METHODS AND PROCEDURES ; PROBLEM SOLVING ; REENTRY VEHICLES ; SUPERSONIC FLIGHT ; SURFACE TEMPERATURE ; Thermodynamics ; TRANSLATIONS ; USSR</subject><creationdate>1967</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>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27567,27568</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0674669$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Matveev,S. K</creatorcontrib><creatorcontrib>FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO</creatorcontrib><title>APPROXIMATE CALCULATION ON NON-STEADY-STATE FUSION OF VITREOUS MATERIALS (PRIBLIZHENNYI RASCHET NESTATSIONARNOGO OPLAVLENIYA STEKLOVIDNYKH MATERIALOV)</title><description>The problem of unsteady ablation of glassy materials subjected to aerodynamic heating is considered. An approximate integral method is outlined for calculating the significant ablation parameters. The method is applied to determining heat transfer rates and surface temperature at the stagnation point of a blunted body. The differential equation derived from the equation of conservation of energy is used to calculate the surface temperature of the melted film. A comparison of the numerical results obtained by this method with the exact solution shows satisfactory agreement. It is said that this method may be used when similar solutions are not valid and successfully applied to calculations of unsteady melting of a glass shield not only in the stagnation region, but also on the surface of the body. (Author)
Edited trans. of Inzhenerno-Fizicheskii Zhurnal (USSR) v11 n6 p730-736 1966.</description><subject>ABLATION</subject><subject>AERODYNAMIC HEATING</subject><subject>APPROXIMATION(MATHEMATICS)</subject><subject>ATMOSPHERE ENTRY</subject><subject>BLUNT BODIES</subject><subject>CERAMIC COATINGS</subject><subject>CERAMIC MATERIALS</subject><subject>DIFFERENTIAL EQUATIONS</subject><subject>Guided Missiles</subject><subject>HEAT SHIELDS</subject><subject>HEAT TRANSFER</subject><subject>NUMERICAL METHODS AND PROCEDURES</subject><subject>PROBLEM SOLVING</subject><subject>REENTRY VEHICLES</subject><subject>SUPERSONIC FLIGHT</subject><subject>SURFACE TEMPERATURE</subject><subject>Thermodynamics</subject><subject>TRANSLATIONS</subject><subject>USSR</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1967</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFjMEKglAQRd20iOoPWsyyFkJQGC0nfebga0bee0q2kSgDIdrot_S9aUTb4MJZHM4dey_MMiMnOqJTEKIOc42OhKEfC_vWKYzKHoOPc_tRMRTkjJLcwtAZQm1hkRnaazonirkkMGjDRDlgNbRDh4blICCZxkIrphKhf0-1FBRxmSa_LymWU290vzzaevblxJvHyoWJf-uaa9V2zbPuKoxWwXYTBLv1H_0GBkxArA</recordid><startdate>19671204</startdate><enddate>19671204</enddate><creator>Matveev,S. K</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>19671204</creationdate><title>APPROXIMATE CALCULATION ON NON-STEADY-STATE FUSION OF VITREOUS MATERIALS (PRIBLIZHENNYI RASCHET NESTATSIONARNOGO OPLAVLENIYA STEKLOVIDNYKH MATERIALOV)</title><author>Matveev,S. K</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD06746693</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1967</creationdate><topic>ABLATION</topic><topic>AERODYNAMIC HEATING</topic><topic>APPROXIMATION(MATHEMATICS)</topic><topic>ATMOSPHERE ENTRY</topic><topic>BLUNT BODIES</topic><topic>CERAMIC COATINGS</topic><topic>CERAMIC MATERIALS</topic><topic>DIFFERENTIAL EQUATIONS</topic><topic>Guided Missiles</topic><topic>HEAT SHIELDS</topic><topic>HEAT TRANSFER</topic><topic>NUMERICAL METHODS AND PROCEDURES</topic><topic>PROBLEM SOLVING</topic><topic>REENTRY VEHICLES</topic><topic>SUPERSONIC FLIGHT</topic><topic>SURFACE TEMPERATURE</topic><topic>Thermodynamics</topic><topic>TRANSLATIONS</topic><topic>USSR</topic><toplevel>online_resources</toplevel><creatorcontrib>Matveev,S. K</creatorcontrib><creatorcontrib>FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Matveev,S. K</au><aucorp>FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>APPROXIMATE CALCULATION ON NON-STEADY-STATE FUSION OF VITREOUS MATERIALS (PRIBLIZHENNYI RASCHET NESTATSIONARNOGO OPLAVLENIYA STEKLOVIDNYKH MATERIALOV)</btitle><date>1967-12-04</date><risdate>1967</risdate><abstract>The problem of unsteady ablation of glassy materials subjected to aerodynamic heating is considered. An approximate integral method is outlined for calculating the significant ablation parameters. The method is applied to determining heat transfer rates and surface temperature at the stagnation point of a blunted body. The differential equation derived from the equation of conservation of energy is used to calculate the surface temperature of the melted film. A comparison of the numerical results obtained by this method with the exact solution shows satisfactory agreement. It is said that this method may be used when similar solutions are not valid and successfully applied to calculations of unsteady melting of a glass shield not only in the stagnation region, but also on the surface of the body. (Author)
Edited trans. of Inzhenerno-Fizicheskii Zhurnal (USSR) v11 n6 p730-736 1966.</abstract><oa>free_for_read</oa></addata></record> |
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| source | DTIC Technical Reports |
| subjects | ABLATION AERODYNAMIC HEATING APPROXIMATION(MATHEMATICS) ATMOSPHERE ENTRY BLUNT BODIES CERAMIC COATINGS CERAMIC MATERIALS DIFFERENTIAL EQUATIONS Guided Missiles HEAT SHIELDS HEAT TRANSFER NUMERICAL METHODS AND PROCEDURES PROBLEM SOLVING REENTRY VEHICLES SUPERSONIC FLIGHT SURFACE TEMPERATURE Thermodynamics TRANSLATIONS USSR |
| title | APPROXIMATE CALCULATION ON NON-STEADY-STATE FUSION OF VITREOUS MATERIALS (PRIBLIZHENNYI RASCHET NESTATSIONARNOGO OPLAVLENIYA STEKLOVIDNYKH MATERIALOV) |
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