Isolated roughness induced boundary-layer transition - Shuttle Orbiter ground tests and flight experience

Bouslog, Stanley A.; Bertin, John J.; Berry, Scott A.; Caram, Jose M.

doi:10.2514/6.1997-274

Cited by 25 publications

(11 citation statements)

References 5 publications

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“…Berry et al 42;43 investigated the in uence of isolated three-dimensional roughness elements on boundary-layer transition for hypersonic ows over both the Space Shuttle Orbiter and X-33 con gurations at high angles of attack. Based on these results, an algebraic correlation was given between the postulated disturbance parameter k=± (roughness height nondimensionalizedby smooth-wall laminar boundary-layer thickness) and the postulated transition parameter Table 2 of Bouslog et al 41 for the Space Shuttle Orbiter geometry range from 11.06 to 19.31, with an average value of 15.39. The value for the constant C in each case was determinedfrom a log-log correlation plot using the coordinates of the algebraic correlation.…”

Section: Lifting-entry Vehiclesmentioning

confidence: 99%

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Review and Synthesis of Roughness-Dominated Transition Correlations for Reentry Applications

Reda

2002

Journal of Spacecraft and Rockets

174

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Nomenclature a = constant; Fig. 1 C, C 0 = constants k = roughness element height, ft N k = average roughness element height, ft L = vehicle length, ft M = Mach number n = exponent; Fig. 1 N R = Poll's transition parameter 29;30 ; Eq. (1) Re ke = roughness Reynolds number based on height k and edge conditions Re kk = roughness Reynolds number based on height k and conditions at k Re µ = Reynolds number based on height µ and edge conditions U = velocity component parallel to test surface or velocity component perpendicularto attachment line, ft /s V = velocity component parallel to attachment line, ft/s X = generalized disturbance parameter or axial coordinate along windward centerline x = coordinate perpendicular to attachment line, ft Y = generalized transition parameter ® = angle of attack, deg ± = smooth-wall laminar boundary-layer thickness, ft = Poll's length scale 29;30 [Eq. (2)], ft µ = smooth-wall laminar boundary-layer momentum thickness, ft ¹ = viscosity, lbm/ft ¢ s º = kinematic viscosity, ft 2 /s ½ = density, lbm/ft 3 Subscripts al = attachment line e = edge of smooth-wall laminar boundary layer k = based on conditions in smooth-wall laminar boundary layer at top of roughness elements tr = transition w = wall or based on wall temperature Superscript ¤ = properties evaluated at Poll's reference temperature 29;30 Daniel C. Reda recently joined the Space Technology Division at NASA Ames Research Center as a Senior Scientist, responsible for aerothermodynamics research to support access-to-space and planetary-entry missions. Previously, he was a Senior Research Scientist in the Ames Research Center Fluid Mechanics Laboratory, where he developed a global surface shear stress vector measurement method using liquid crystal coatings.

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Section: Lifting-entry Vehiclesmentioning

confidence: 99%

“…2. Table 2 of Bouslog et al 41 was used to provide the required information concerning conditions in the smooth-wall laminar boundary layer at the roughness height. Except for the two lowest disturbance parameter data points, this isolated roughness data set is well tted by…”

Section: Lifting-entry Vehiclesmentioning

confidence: 99%

Review and Synthesis of Roughness-Dominated Transition Correlations for Reentry Applications

Reda

2002

Journal of Spacecraft and Rockets

174

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“…As noted in Ref. 25, the majority of the early flight transition times have been the result of the TPS gap fillers sticking out (protuberances). However, since the new BLT Tool is intended to disposition both protuberances and cavities, the existing data will need to be examined again in hopes of providing credible cavity transition data.…”

Section: Blt Task Developmentmentioning

confidence: 99%

“…To develop the wind tunnel correlation of the boundary layer results, nearly four-dozen computational solutions were required to cover the three LaRC facilities, multiple angles of attack, and the range of Reynolds numbers. Additionally, there was an existing protuberance database previously obtained in the Arnold Engineering and Development Center (AEDC) Tunnel B on a 1.8% Orbiter model (from 1996) 25 A few of the previous attempts at analyzing the flight data are reported in Refs. 7, 28, and 29.…”

Section: Blt Task Developmentmentioning

confidence: 99%

Overview of Boundary Layer Transition Research in Support of Orbiter Return to Flight

Berry

Horvath

Greene

et al. 2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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A predictive tool for estimating the onset of boundary layer transition resulting from damage to and/or repair of the thermal protection system was developed in support of Shuttle Return to Flight. The boundary layer transition tool is part of a suite of tools that analyze the aerothermodynamic environment to the local thermal protection system to allow informed disposition of damage for making recommendations to fly as is or to repair. Using mission specific trajectory information and details of each damage site or repair, the expected time (and thus Mach number) at transition onset is predicted to help define the aerothermodynamic environment to use in the subsequent thermal and stress analysis of the local thermal protection system and structure. The boundary layer transition criteria utilized for the tool was developed from ground-based measurements to account for the effect of both protuberances and cavities and has been calibrated against select flight data. Computed local boundary layer edge conditions were used to correlate the results, specifically the momentum thickness Reynolds number over the edge Mach number and the boundary layer thickness. For the initial Return to Flight mission, STS-114, empirical curve coefficients of 27, 100, and 900 were selected to predict transition onset for protuberances based on height, and cavities based on depth and length, respectively.

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“…They found that over half of the early transition cases would likely be asymmetric. Bouslog et al 13 provides additional flight results (including two of the very early transition flight cases, STS-28 and 73) with comparison to ground-based data.…”

Section: Introductionmentioning

confidence: 99%

Review of Orbiter Flight Boundary Layer Transition Data

McGinley

Berry

Kinder

et al. 2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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In support of the Shuttle Return to Flight program, a tool was developed to predict when boundary layer transition would occur on the lower surface of the orbiter during reentry due to the presence of protuberances and cavities in the thermal protection system. This predictive tool was developed based on extensive wind tunnel tests conducted after the loss of the Space Shuttle Columbia. Recognizing that wind tunnels cannot simulate the exact conditions an orbiter encounters as it re-enters the atmosphere, a preliminary attempt was made to use the documented flight related damage and the orbiter transition times, as deduced from flight instrumentation, to calibrate the predictive tool. After flight STS-114, the Boundary Layer Transition Team decided that a more in-depth analysis of the historical flight data was needed to better determine the root causes of the occasional early transition times of some of the past shuttle flights. In this paper we discuss our methodology for the analysis, the various sources of shuttle damage information, the analysis of the flight thermocouple data, and how the results compare to the Boundary Layer Transition prediction tool designed for Return to Flight. Nomenclature

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Isolated roughness induced boundary-layer transition - Shuttle Orbiter ground tests and flight experience

Cited by 25 publications

References 5 publications

Review and Synthesis of Roughness-Dominated Transition Correlations for Reentry Applications

Review and Synthesis of Roughness-Dominated Transition Correlations for Reentry Applications

Overview of Boundary Layer Transition Research in Support of Orbiter Return to Flight

Review of Orbiter Flight Boundary Layer Transition Data

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