Aerothermodynamic Testing of Protuberances and Penetrations on the NASA Crew Exploration Vehicle Heat Shield

Liechty, Derek S.

doi:10.2514/6.2008-1240

Cited by 12 publications

(13 citation statements)

References 5 publications

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“…The model's maximum diameter of 17.78 cm (7.00-in) was chosen for consistency with previous CEV tests (Refs. 5,6) and to allow testing of this model in NASA Langley Research Center 20-Inch Mach 6 Air Tunnel. The model was designed to permit substitution of a removable insert piece on the lower half of the forebody heat-shield.…”

Section: Wind Tunnel Model Designmentioning

confidence: 99%

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Aeroheating Testing and Predictions for Project Orion CEV at Turbulent Conditions

Hollis

Berger

Horvath

et al. 2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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Inch Mach 6 Air Tunnel. Laminar and turbulent predictions were generated for all wind tunnel test conditions and comparisons were performed with the experimental data to help define the accuracy of computational method. In general, it was found that both laminar data and predictions, and turbulent data and predictions, agreed to within less than the estimated ±12% experimental uncertainty estimate. Laminar heating distributions from all three data sets were shown to correlate well and demonstrated Reynolds numbers independence when expressed in terms of the Stanton number based on adiabatic wallrecovery enthalpy. Transition onset locations on the leeside centerline were determined from the data and correlated in terms of boundary-layer parameters. Finally turbulent heating augmentation ratios were determined for several body-point locations and correlated in terms of the boundary-layer momentum Reynolds number. = free stream Mach number Me = boundary-layer edge Mach number

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Section: Wind Tunnel Model Designmentioning

confidence: 99%

“…As shown in Figure 7, St(Re ,, ) 5 can be used to approximately correlate laminar heat-flux distributions over the range of test conditions. Transitional/turbulent data can clearly be identified when the values diverge from the lower Reynolds number data, which are nearly constant.…”

mentioning

confidence: 99%

Aeroheating Testing and Predictions for Project Orion CEV at Turbulent Conditions

Hollis

Berger

Horvath

et al. 2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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“…These pads did not include the tension ties, although data on their effects were documented in Ref. 7. Two CEV configuration models, CEV-1X and CEV-2X, were tested.…”

Section: Figure 1 Nasa Crew Exploration Vehicle (Conceptual Artwork)mentioning

confidence: 99%

Heating Augmentation in Laminar Flow Due to Heat-Shield Cavities on the Project Orion CEV

Hollis

2008

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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An experimental study has been conducted to assess the effects of compression pad cavities on the aeroheating environment of the Project Orion CEV heat-shield at laminar conditions. Testing was conducted in Mach 6 and Mach 10 perfect-gas wind tunnels to obtain heating measurements on and around the compression pads using global phosphor thermography. Consistent trends in heating augmentation levels were observed in the data and correlations of average and maximum heating at the cavities were formulated in terms of the local boundary-layer parameters and cavity dimensions. Additional heating data from prior testing of Genesis and Mars Science Laboratory models were also examined to extend the parametric range of cavity heating correlations.

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“…1 Tension ties that hold the capsule to the launch vehicle will be cylindrical. The length of these ties considerably exceeds their diameter.…”

Section: Introductionmentioning

confidence: 99%

High-Speed PLIF Imaging of Hypersonic Transition over Discrete Cylindrical Roughness

Danehy

Ivey

Inman

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Transitional flow over cylindrical protuberances attached to a flat plate has been studied in a hypersonic wind tunnel. The tests were performed in the 31-Inch Mach 10 Air Tunnel at NASA Langley Research Center. Cylindrical protuberances with 4-mm diameter and heights of 1, 2, and 4 mm, were attached to the flat plate. The plate angle of attack and tunnel stagnation pressure were varied to achieve desired combinations of boundary layer edge Mach number and the boundary layer thickness. Several different types of flow visualization based on nitric oxide planar laser-induced fluorescence (NO PLIF) were used. A 10-Hz NO PLIF system was used to produce a thin laser sheet. This laser sheet was oriented perpendicular to the flat plate on some runs and parallel to the flat plate on others. A thick laser sheet was also used in some runs to provide visualization of entire flow structures inside the boundary layer. Viewing the PLIF intensity generated with the thick laser sheet using two cameras allowed stereoscopic visualization of the flow. In post processing, these images were combined to produce anaglyphs. Viewing these anaglyphs through blue and red 3D-glasses allows the three-dimensional flow structures to be observed. Another measurement system was a MHz-rate NO PLIF imaging system. Both PLIF measurement systems have better than one microsecond time resolution, which is fast enough to freeze the flow. The MHz system allows subsequent images to be obtained at one or two microsecond time intervals, resulting in movies of the flow. The data reported in this paper show the size, shape, and speed of flow structures in transitional hypersonic boundary layer flows and will provide valuable comparison data for computations of these flows.

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Aerothermodynamic Testing of Protuberances and Penetrations on the NASA Crew Exploration Vehicle Heat Shield

Cited by 12 publications

References 5 publications

Aeroheating Testing and Predictions for Project Orion CEV at Turbulent Conditions

Aeroheating Testing and Predictions for Project Orion CEV at Turbulent Conditions

Heating Augmentation in Laminar Flow Due to Heat-Shield Cavities on the Project Orion CEV

High-Speed PLIF Imaging of Hypersonic Transition over Discrete Cylindrical Roughness

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