Viking Afterbody Heating Computations and Comparisons to Flight Data

Edquist, Karl T.; Wright, Michael J.; Allen, Gary

doi:10.2514/6.2006-386

Cited by 28 publications

(18 citation statements)

References 20 publications

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“…The results of this analysis indicated that the wake flowfield was predicted to be unsteady even at low Reynolds number. 94 As shown in Fig. 22, the temporally averaged computational results generally underpredict the measured heating rates (by as much as a factor of three), particularly on the aluminum base cover near the peak heating point.…”

Section: A Mars Viking I and Iimentioning

confidence: 92%

“…The high heating levels, as well as the slope change observed in heating rate vs. Reynolds number at Re D ~ 5x10 5 , were believed to be evidence of turbulent transition on the base. 121 Edquist et al 94 recently reanalyzed the thermocouple data and explored the impact of material response and entry trajectory uncertainties on the resulting measured heating rates. In addition, detailed CFD simulations were performed with two different codes at eleven points along the entry trajectory for Viking I.…”

Section: A Mars Viking I and Iimentioning

confidence: 99%

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A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

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

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The current status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a predominantly CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Localized heating due to penetrations or other singularities on the aeroshell must also be taken into account. The physical models employed to predict these phenomena are reviewed, and key uncertainties or deficiencies inherent in these models are explored.

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Section: A Mars Viking I and Iimentioning

confidence: 92%

Section: A Mars Viking I and Iimentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

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

Self Cite

View full text Add to dashboard Cite

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“…Nevertheless, large uncertainties were included in the design conditions and SLA-561V was chosen to mitigate concerns about interference effects from RCS thruster plumes. 29 was made previously to compare CFD-based heat flux to the Viking data at two discrete locations. Time-averaged laminar LAURA and DPLR super-catalytic heating was up to 80% below heat flux derived from the flight temperature data.…”

Section: Resultsmentioning

confidence: 99%

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

Edquist

Dyakonov

Wright

et al. 2009

41st AIAA Thermophysics Conference

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Aerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule backshell and parachute cone. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux) design entry trajectories from a 2009 launch. Transient interference effects from reaction control system thruster plumes were included in the design environments when necessary. The limiting backshell design heating conditions of 6.3 W/cm 2 for heat flux and 377 J/cm 2 for total heat load are not influenced by thruster firings. Similarly, the thrusters do not affect the parachute cover lid design environments (13 W/cm 2 and 499 J/cm 2 ). If thruster jet firings occur near peak dynamic pressure, they will augment the design environments at the interface between the backshell and parachute cone (7 W/cm 2 and 174 J/cm 2 ). Localized heat fluxes are higher near the thruster fairing during jet firings, but these areas did not require additional thermal protection material. Finally, heating bump factors were developed for antenna radomes on the parachute cone.lift-to-drag ratio m entry system mass (kg) p pressure (Earth atm, 1 Earth atm = 101,325 P a)

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“…LAURA has been used extensively to predict the aerodynamics and aerothermodynamics for Mars entry vehicles [2][3][4][19][20][21][22] . Perfect gas air conditions were used for the wind tunnel conditions and a finite-rate chemistry model was used for the flight conditions.…”

Section: Methodsmentioning

confidence: 99%

Viking Afterbody Heating Computations and Comparisons to Flight Data

Cited by 28 publications

References 20 publications

A Review of Aerothermal Modeling for Mars Entry Missions

A Review of Aerothermal Modeling for Mars Entry Missions

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

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