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Reentry Reports

Collected here are early reports on reentry heatshield and reentry wake observables technology. Some are not available in the general literature, but they were published as unclassified company reports. All of these reports were scanned, but links to pdf files are given only after permission to post has been granted. Permission to post these documents must be granted either by a publisher or by the company in which reports were written or the company into which it has been merged. Permission to post the reports linked has been granted by Lockheed - Martin, by ASME and by Northrop Grumman.

AuthorTITLEActionComments
Wallace D. Hayes
Hypersonic Flow Fields at Small Density Ratio
May 12, 1955		 hayes.pdf An approximate method for calculating the inviscid shock layer.
Lester Lees
Laminar Heat Transfer Over Blunt-Nosed Bodies at Hypersonic Speeds
June 8, 1955		lees-1.pdf Includes "real gas"effects and many useful approximations.
M. Richard Denison
Turbulent Boundary Layer on Blunt Bodies of Revolution At Hypersonic Speeds
April 13, 1956		turb.pdf First analysis showing that peak turbulent heating on a blunt nose is near the sonic point in the flow outside the boundary layer.
M. R. Denison and D. A DooleyCombustion in the Laminar Boundary Layer of Chemically Active Sublimators
September 23, 1957		lam.pdf One of the first analyses of graphite heat shields.
C. B. Cohen, R. Bromberg, and R. P. LipkisBoundary Layers with Chemical Reactions Due to Mass Additions
October 1957		cbl.pdf Another Early Analysis of Chemical Reactions in the Boundary Layer.
Lester Lees
Convective Heat Transfer with Mass Addition and Chemical Reactions
March 1958		lees-2.pdf Includes laminar and turbulent flow, simple conclusions for Lewis Number unity, "heat blocking" effects, and many references.
M. R. Denison Combustion in the Turbulent Boundary Layer of Chemically Active Sublimators
March 10, 1958		turb-carb.pdf One of the first analyses of graphite heat shields in turbulent flow.
E. P. Bartlett and M. R. Denison Experimental Ablation Rates in a Turbulent Boundary Layer
1960		expasme.pdf Experiments were conducted on ablation of graphite in up to 100% oxygen to simulate the high heating rates of reentry. Results verify turbulent combustion analysis previously developed.
M. Richard Denison Analysis of Flush Electrostatic Probes for Reentry Measurements
September 1967		probes.pdf Analysis of collision dominated electrostastic probes whose collecting surfaces are flush with the external surface of a slightly blunted reentry vehicle.
Eric Baum and M. Richard Denison A Thick Sheath Boundary Layer Model for Conical Electrostatic Probes in a Continuum Flow
September 1970		cone-probe.pdf Applies to negatively biased conical probes in a slightly ionized, chemically frozen, continuum supersonic flow. Good agreement with experimental data is obtained.
Stanley G. Howard Wake Radar Amplitude Prediction Technique
December 20, 1971		wake-radar.pdf A simplified technique for determining the electron density in the flow field and the resultant wake radar cross section of a reentry vehicle.

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