Convective and radiative heat transfer during superorbital entry

Hoshizaki, H.; Wilson, K. H.

doi:10.2514/6.1966-106

Cited by 14 publications

(3 citation statements)

References 4 publications

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“…In light of recent opacity calculations, 3 the step models employed in the present analysis do not fully simulate the large optical thickness characteristic of the vacuum ultraviolet. This is evident by comparing in Fig. 3 the nongray step model results, which vary approximately as R°-7 , with the detailed results of Hoshizaki and Wilson, 3 which vary approximately as R 0 -5 . On the other hand, it is interesting to note that the present approximate results do provide a reasonable prediction for radiative heat transfer for nose radii between 1 and 4 ft at the flight condition considered.…”

Section: Discussionmentioning

confidence: 70%

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Nongray radiative stagnation point heat transfer.

Anderson¹

1968

AIAA Journal

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Section: Discussionmentioning

confidence: 70%

“…3 A thorough bibliography has been given by Hansen. 4 This Note is concerned with an investigation of similar solutions of the threedimensional, compressible, laminar boundary layer in Cartesian coordinates.…”

Section: Similarity Solutions Of the Threedimensional Compressible mentioning

confidence: 99%

Nongray radiative stagnation point heat transfer.

Anderson¹

1968

AIAA Journal

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“…Each of these test specimens were covered with a 0.0025-in.-thick polyvinyl chloride (PVC) skin (Hooker Chemical Company) similar to that used by Looney and Blick. 1 Water level was adjusted so that the PVC skin was barely touching the resiliant materials under it during the water-saturated foam tests. After installation, various tensions were applied to the PVC skin by means of weights at the front and rear ends and by springs at the sides.…”

Section: Compliant Surface Test Specimensmentioning

confidence: 99%

Radiation absorption effects on heating loads encountered during hyperbolic entry.

Engel¹,

Spradley²

1969

Journal of Spacecraft and Rockets

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_" 0004-o HARD PLATE V 40PPI WW 0.132 Ib/IN (Tz) O 40PPI WW 0.26 Ity/IN (Tz) A 40PPI WW 0.1975 IbyiN (Tz) 10 30 5O 7O 90 IIO 130 150 I7O 190 210 230 VELOCITY (FPS) Fig. 3 Skin-friction coefficients vs velocity for 40-PPI coating.along the test plate and by calculating the bending moment induced by these pressures. The turbulence intensity of the tunnel ranged from approximately 2% at 20 fps, 0.7% at 05 fps, to 0.3% at 180 fps. Compliant Surface Test SpecimensOne-inch-thick, 27-pores-per-inch (27 PPI) polyurethane foam and -g^-in.-thick, 40-PPI polyurethane foam manufactured by Scott Paper Company and Precision Rubber and Plastic Company, respectively, were used as two of the substrate materials. The third type of compliant coating did not use a polyurethane substrate but used a ^-in. layer of plain water. The substrates were held in place by a shallow aluminum plate with J-in.-thick sidewalls. Each of these test specimens were covered with a 0.0025-in.-thick polyvinyl chloride (PVC) skin (Hooker Chemical Company) similar to that used by Looney and Blick. 1 Water level was adjusted so that the PVC skin was barely touching the resiliant materials under it during the water-saturated foam tests. After installation, various tensions were applied to the PVC skin by means of weights at the front and rear ends and by springs at the sides. Initially weights were used for side tension but this caused excessive vibration of the test plate. ResultsMeasured turbulent skin-friction drag coefficients are shown in Figs. 2-4. The tunnel was operating at 17 to 230 fps. The corresponding Reynolds numbers were 4.4 X 10 5 to 4.8 X 10 6 . Since there was no exact method to determine the characteristic length for a curved tunnel floor, an approximate length of 4.5 ft [Li in Eq. (1)] was used to calculate Reynolds number. Using the following formula: (i) O 0.003 2 O K O = 0.002 O HARD PLATE D PVC WATER SUBSTRATE 0.316 lbf/IN (Tz) 20 30 REYNOLDS NO. (XV/^) x 10 s 10 30 50 70 90 IIO 130 I5O 170 190 210 230 VELOCITY (FPS) Fig. 4 Skin-friction coefficients vs velocity for water substrate coating.the average skin-friction coefficient over the test plate was calculated and was found to fall close to the hard plate experimental data as shown in Fig. 4. Equation (1) was obtained by an integration of the local turbulent skin-friction equation. 3 L 2 in Eq. (1) is the length of the test plate. In Fig. 2, for the dry PVC-polyurethane tests, no data were shown for speeds higher than 86 fps. The PVC skin formed a standing wave at 86 fps. The same reason was true for the cutoff in Fig. 4 for the PVC-water layer tests. No standing waves were observed for water-saturated polyurethane tests.For 27-PPI WW (saturated with water) the highest reduction in C F was 28% below hard plate C F at 100 fps, and for 40-PPI WW the maximum reduction was 38% at 220 fps. The uncertainty in the skin-friction data points in Figs. 2-4 is approximately = 0.0001. ConclusionsAppreciable reduction in flat-plate turbulent airflow skinfriction coefficients has been demonstrated ...

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Ionization nonequilibrium effects on a radiating shock layer

Sabetta¹,

Cunsolo²,

Cenedese³

1975

The Physics of Fluids

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The stagnation region of a shock layer in front of a blunt body re-entering the atmosphere at high altitude and high velocity is considered. At these flight conditions the ionization is out of equilibrium in a considerable fraction of the shock layer thickness. The nonequilibrium phenomenon modifies the distribution of all the thermodynamic, radiative, and transport properties of the gas. To quantitatively evaluate these modifications and their influence upon the radiative heat flux, the governing equations for nonequilibrium conditions are obtained and numerically solved for real air. A simple method of evaluating nonequilibrium absorption and emission coefficients is also proposed. The numerical results show that, while nonequilibrium slightly affects the body heating load, important variations occur in the shock layer structure and the radiative flux emergent at the shock front is considerably reduced with respect to complete equilibrium conditions. This fact must be taken into account in all studies dealing with precursor effects.

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Convective and radiative heat transfer during superorbital entry

Cited by 14 publications

References 4 publications

Nongray radiative stagnation point heat transfer.

Nongray radiative stagnation point heat transfer.

Radiation absorption effects on heating loads encountered during hyperbolic entry.

Ionization nonequilibrium effects on a radiating shock layer

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