Accession Number : AD0475777


Title :   CONVECTIVE STAGNATION POINT HEATING FOR REENTRY SPEEDS UP TO 70,000 FEET/SECOND INCLUDING EFFECTS OF LARGE BLOWING RATES (TASK 3.1: FLOWFIELD ANALYSIS -- REST PROGRAM).


Descriptive Note : Technical memo.


Corporate Author : AVCO CORP WILMINGTON MA RESEARCH AND ADVANCED DEVELOPMENT DIV


Personal Author(s) : DeRienzo, Philip ; Pallone, Adrian


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/475777.pdf


Report Date : 05 Jan 1965


Pagination or Media Count : 67


Abstract : The current state-of-the-art is reviewed with respect to the calculation of convective stagnation point heating at supersatellite reentry speeds. Recently calculated transport properties have been compared with experiment. It is noted that theoretical and experimental estimates of the total thermal conductivity are in much closer agreement than reported by earlier investigators. Similarity solutions employing these recently computed transport properties are presented for the convective heat transfer rate in an ionized, dissociated gas for equilibrium air and equilibrium nitrogen at reentry speeds up to 70,000 feet/sec. Solutions are also obtained for the case when large rates of injection are introduced at the stagnation point. Tables of boundary layer characteristics including profiles of temperature, velocity, and enthalpy are presented for the axisymmetric and two-dimensional stagnation point.


Descriptors :   *REENTRY VEHICLES , VELOCITY , ABLATION , INJECTION , TEMPERATURE , EXPERIMENTAL DATA , ATMOSPHERE ENTRY , STATE OF THE ART , AIR , REPORTS , BOUNDARY LAYER , NITROGEN , TRANSPORT PROPERTIES , FLOW FIELDS , THERMAL CONDUCTIVITY , TABLES(DATA) , TWO DIMENSIONAL FLOW , CONVECTION(HEAT TRANSFER) , HYPERSONIC CHARACTERISTICS , ENTHALPY , GAS IONIZATION , STAGNATION POINT , AXISYMMETRIC FLOW


Subject Categories : Guided Missiles
      Fluid Mechanics
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE