Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 230
... Pressure probes have shown that the total pressure inside the shock envelope is 2.2 atm . These data , along with the test chamber static pressure of 1 atm , lead to a Mach number determination of 1.25 . Using the freestream centerline ...
... Pressure probes have shown that the total pressure inside the shock envelope is 2.2 atm . These data , along with the test chamber static pressure of 1 atm , lead to a Mach number determination of 1.25 . Using the freestream centerline ...
Page 272
... Pressure and temperature distribution on a flat plate at 25 in . from motor B. CONTOUR SCALE 1-10 psia 2-20 psia 3-30 psia 4-40 psia 5-50 psia 6-100 psia ROCKET MOTOR Fig . 9 Pressure contours for motor A booster impinging into a two ...
... Pressure and temperature distribution on a flat plate at 25 in . from motor B. CONTOUR SCALE 1-10 psia 2-20 psia 3-30 psia 4-40 psia 5-50 psia 6-100 psia ROCKET MOTOR Fig . 9 Pressure contours for motor A booster impinging into a two ...
Page 349
... pressure boundary condition . Typical results are shown in Fig . 2 , where lines of constant temperature and pressure are illustrated . This field serves as the boundary for the sub- sequent tailoring of a shear - layer profile , as ...
... pressure boundary condition . Typical results are shown in Fig . 2 , where lines of constant temperature and pressure are illustrated . This field serves as the boundary for the sub- sequent tailoring of a shear - layer profile , as ...
Contents
Effects of Atmospheric Structure on Radiative Heating | 3 |
Radiative Flux Penetration through a Blown Shock Layer | 22 |
Approximate Inviscid Radiating Flowfield Analysis | 42 |
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Common terms and phrases
ablation absorption coefficient AIAA AIAA Journal AIAA Paper altitudes analysis angle of attack base blockage body surface boundary layer bow shock calculations carbon phenolic chemical chemical equilibrium computed configuration correlation distribution energy enthalpy entry conditions equilibrium experimental flow flowfield freestream graphite H₂ heat shield Heat Transfer heat-transfer hydrogen hyperboloid inertial entry angle intensity inviscid Jupiter Jupiter entry km/sec laminar laser mass loss mass transfer material mixture model atmospheres MW/m² NASA nominal nondimensional nonequilibrium number density obtained Outer Planet Entry parameters PRECURSOR EFFECT precursor heating precursor region predicted present pressure radiation radiative and convective radiative flux radiative heat flux radiative heating rates recession Reynolds number shock-layer shown in Fig silica solution species spectral spectral flux sphere-cone stagnation point stagnation-point temperature thermal thermochemical thermodynamic tion trajectory turbulent uncertainty variation velocity viscous shock-layer VSL3D wall