1

PRESENT CHALLENGES IN NASAPRESENT CHALLENGES IN NASA’’s s AEROSCIENCES DISCIPLINEAEROSCIENCES DISCIPLINE

David M. Schuster, PhDNASA Technical Fellow for AerosciencesNASA Engineering and Safety Center

High-Performance Computing ForumApril 15, 2008Norfolk, VA

2

NASA’s Missions and Links to the Aerosciences Discipline

• The NASA Technical Fellows are responsible for assessing the state of and providing stewardship for their respective disciplines.– A NASA-centric evaluation.– An assessment of the discipline

to address the technical challenges within the individual NASA Missions.

• Challenges in the four missions revealed three primary Aerosciences issues facing NASA.

ExplorationSystems

NASA’s Missions

AeronauticsResearch

SpaceOperations

Science

3

NASA Aerosciences in Brief

• Aerosciences is in high demand across the Agency.

• Actively leveraging the surge in computational capability and tailoring ground and flight testing to merge with this capability.– No longer simply validating

methods using experiments.– Computations employed to

minimize and focus test matrices and reduce vehicle development cycle times.

• Aerosciences is far from a mature science, with many of the present challenges resulting from interactions with other disciplines.– Thermal, Loads and Dynamics, GN&C, Structures, Acoustics, and Propulsion

are among our primary interaction disciplines.• NASA’s Constellation Program is presenting new challenges.

– Sharp angles, protuberances, and jet interactions can generate unsteady, separated flows that contribute to aeroacoustic and buffet environments.

4

CEV LaunchAbort System

Aerosciences High Demand Areas

• Aerodynamic Database Construction.– Aerodynamic Performance.– Loads and Dynamics.– Guidance, Navigation, and Control.

• Aero-Interactions.– Aerothermodynamics.

• Aeroheating.– Aeroacoustics.

• Environments.– Aeroelasticity.

• Unsteady aerodynamics.– Aeropropulsion.

• Integration.• Plume interaction.

Red indicates areas where holes in capability exist leading to research and technology integration opportunities.

CEVAerothermodynamics

5

Aeroscience Capability Shortfalls

Three aeroscience areas are currently hindering the prediction of environments and performance for NASA flight vehicles.

(In order of criticality)

1. Prediction, characterization and quantification of unsteady, separated flows• Testing is very expensive and time-consuming• Acoustics and buffet loads estimation require accurate

characterization of these flows.2. Assessment of Aero-thermodynamic Environments.

• Spacecraft ascent/reentry, hypersonic air vehicles.• High-Mach boundary layer transition, ablative TPS performance.

3. Aero-propulsion interaction.• Aero-plume interactions, reaction control systems, hypersonic air

vehicle propulsion systems.

6

Unsteady Separated Flow Computations

• Reynolds Averaged Navier-Stokes solvers are relatively capable of predicting large-scale separated flows such as those found in Strouhal Vortex shedding.– Flows involving smaller scale eddies quickly

become intractable due to modeling and computation times.

• Advanced modeling techniques such as Detached Eddy Simulation (DES) can significantly reduce the size of eddies that can be captured and extend the capabilities of computations.– Limited experience with these techniques and computational resources are

still significant.• Interesting flow cases are mildly separated and incipient separated

flows.– Require modeling of eddies smaller than those simulated by DES.

Ares First StageSeparation Aerodynamics

7

STS-114 PAL Ramp Foam Loss

8

Unsteady, Separated Flow PredictionExample: Shuttle Cable Tray Buffet Loads

FLOW

External Tank Surface

LO2 Cable

Tray

Possible Oscillating Shock

Complex Vortex Shedding

9

Simulation of Cable Tray Vortex Shedding(Present RANS Technology)

10

AEDC Test Results Compared with Computed Strouhal Vortex Shedding Oscillations about the

LO2 Cable Tray CFL3D code (2-D): unsteady, viscous

90 deg crossflow simulation

0.2 0.4 0.6 0.8 10

200

400

600

800

1000

1200

1400

2D Unsteady CFD, Inviscid Floor2D Unsteady CFD, Viscous FloorAEDCdata, Unsteady Floor Pres. 11

Mach Number

Freq

uenc

y,H

z

Mach Numbertime, sec time, sec

CN

CN

f, Hz

0.2 0.4 0.6 0.8 10

200

400

600

800

1000

1200

1400

2D Unsteady CFD, Inviscid Floor2D Unsteady CFD, Viscous FloorAEDCdata, Unsteady Floor Pres. 11

Mach Number

Freq

uenc

y,H

z

Mach Numbertime, sec time, sec

CN

CN

f, Hz

• CFD can accurately predict boundaries and frequencies of large-scale vortex shedding events.

• Small-scale fluctuations due to separated flow and turbulence limit the ability of computational methods to accurately predict amplitudes.

• Moving computations to this next level of physics detail is a significant challenge for HPC.

– Computation time, memory, storage, post-processing results.

11

STS-114 Gap Filler Removal

• August 3, 2005: Steve Robinson performs an unplanned EVA to remove a protruding gap filler.

• EVA necessitated by Aeroscience discipline’s inability to confidently predict reentry heating due to protruding gap filler.

12

Forced Transition Shuttle Experiment

• Series of Shuttle flights with modified tiles to artificially trip boundary layer on wing lower surface.

• Controlled high-enthalpy transition data.– Three levels of

experiment complexity.– Modifications include

boundary layer trip and additional instrumentation.

– Remote imaging is also underinvestigation.

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FLOW

HALO II

WAVE

CAST GLANCE

13

HyBoLT Experiment

• Payload launched on ATKALV/X-1 developmental launchvehicle.

• Side A - Natural transition.• Side B – Tripped transition.• Data acquired between Mach

2.5 and Mach 7.5.• Launch from Wallops Flight

Facility.

14

Orion Aerothermal Environment

15

Orion Crew Module Aerothermodynamic Database Construction

16

Aero-Propulsion Interaction

• Interest in aero-propulsion interaction began growing in the 1970’s with the development of powered-lift systems.

• Continued into the 1980’s and 1990’s with the National Aerospace Plane Program.– More focused hypersonic program

continuing today.• Problems continue to be

manifested in spacecraft design in the form of rocket and reaction control system plume interactions with spacecraft and their associated aerodynamics.

17

• Analysis requires additionof physics not traditionallyfound in aeroscience predictions.– Wide temperature and speed

variations within the simulation.– Propulsion by-products.– Reacting flows.

• Computations are expensive and immature.– High operation counts due to added physics.– Stiffness in governing equations.

• Testing is complex and costly.– Plumbing.– Hot gases.

Aero-Propulsion Interaction Challenges

CEV LAV Abort and Control Motors Firing

CEV LAVAbort ControlMotor Firing

18

Observations

• Aerosciences holds key, if not driving, roles in NASA’s missions.– Operation in and transition out of and into atmospheres are critical

aspects of all NASA Mission directorates.• High Performance Computing is an enabling tool allowing

NASA to develop and apply the Aerosciences methods that are designing the vehicles that will take man beyond low earth orbitfor the first time in over 30 years.– NASA has established a strong synergy between computation, ground,

and flight testing that leverages the strengths of each to reduce engineering costs and design cycle times.

• Significant challenges continue to press High Performance Computing environments.– Unsteady flow computations, chemically reacting, and other

multiphysics flows require a new level of computing capability.• Computing speed, memory, and mass storage are the typical areas for

enhancement.– Post-processing is already an issue.

• Long download times for simulations.• Volume of data is outstripping desktop capabilities for model and result

displays and processing.