CFD Applications using Wind-US - Glenn Research Center · CFD Applications using Wind-US ... Supersonic Cruise Nozzle Validation case for NASA’s Next ... (DOE methods) – Off-design

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Glenn Research Center

GTX Inlet

• Rocket-Based Combined Cycle (RBCC) Concept for single-stage to orbit (SSTO)

• Steady-state analyses

• Inlet Flow (Mach 6)– Support tunnel tests

– Examine design options

– Examine unstart sensitivities

– Examine bleed options

Researcher: John Slater (Inlet Branch)

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3D Subsonic InletsDesign study on geometric parameters for 3D subsonic inletsResearcher: John Abbott (Inlet Branch)

Lower Lip Extension, LS/RDE

Con

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1.15

1.2

1.25

1.3

1.35

0 0.25 0.5 0.75 1

αSEP=24o 26o 28o 32o 34o 36o

Static Upper LipSeparation

30o

Cruise Upper LipSeparation

V=1.75 V=2.00 V=2.25

38o40o

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Active Inlet flow Control for Ultra-Intelligent Inlet/Engine Systems

Output:Tailored Inlet FlowField for OptimizedEngine Performance& Operability

Independently ControlledEffector Arrays 1% Fan Bleed

Off

On

Inlet Control

•Neural Net Models•Closed Loop Control

•Inlet•Variables:•Geometry•Inlet Air Flow•Mach Number•Angle of Attack•Sideslip

DistributedSensors ProvideFlow State Map

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Modifications to increase test section to Mach 4

Existing Throat

Modified Throat


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Tandem Fan Nacelle

Matched design mass flow.

Streamlines stagnate above cowl highlight; however, no separation.

Uniform total pressure profile at fan face.

Fan Mach = 0.2636

Recovery: 0.9989

Mach contours


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Rocket Engine Exhaust

H2-O2 RocketPt = 500 psi, Tt=5540 R Cooled Panel

Ambient Air

Frozen chemistry, sevenspecies.

SST turbulence model.Mach contours shown.

Used to compute heattransfer from plume tocooled panel.

Good agreement with data.

Researcher: Nick Georgiadis (Nozzle Branch)

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Supersonic Cruise Nozzle

Validation case for NASA’s NextGeneration Launch Technology.

Reference NASA LaRC nozzle atoff-design conditions.

SST turbulence model.Very good separated flow prediction.

Researcher: Teryn DalBello (Nozzle Branch)

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Jet Noise Prediction

Researcher: Danielle Koch (Acoustics Branch)

Normalized Turbulence Kinetic Energy Distributions, Mach 0.9

PIV Data / WIND Predictions Acoustic Data / MGBK Predictions

- Jet noise predictions generated using WIND, and MGBKaeroacoustic code.

- Mean flow and k–ε results from WIND are input to MGBK.- Accurate prediction of location and magnitude of turbulence

kinetic energy is important if the mean flow results are usedto estimate jet noise.

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Stanitz Elbow

• 90o rectangular elbow (Stanitz et al., NACA, 1953)

• Incompressible flow (Mach 0.26)

• Secondary flow without separation

• Simple geometry and accurate grid

• Inflow BC matches inflow boundary layer

• Outflow BC matches mass flow

• Data (Stanitz et al., 1953)– Inflow boundary layer profile

– Surface static pressures

– Rake total pressure contours

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NASA VDC Inlet• M∞ = 2.35 ⇒ supersonic

• Mixed-compression inlet

• Axisymmetric CFD model

• No leaves, VGs, or struts

• Bleed slot (2.545% flow)

• Nozzle at exit for outflow– Match back-pressure of data

• Data (Saunders et al., 1993)– Centerbody static pressures

– Cowl static pressures

– Pressure recovery

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CFD Objectives – Shock structure– Steady-state performance– Recovery –vs- mass flow

(cane curve)– Spillage– Bleed locations and amount– Best cowl lip and slot

configuration (DOE methods)– Off-design (Mach, α)

Parametric Inlet

Analyses has demonstrated need for:– Bleed models (adjustable mass flow)– Vortex generator models– Outflow boundary conditions


External-compression, supersonic inlet

CFD used the design

CFD supporting testing and validation

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“Optimized” Bleed Cane Curve

93.4%

92.0%

90.4%

88.2%

85.1%

DOE study improved the performance of the inlet over the engine flow sweep

Pslot = 3.5 psi, Pcorner= 4.0, Φaft = 30%

x39

x70

0.70

0.75

0.80

0.85

0.90

0.95

1.00

84 86 88 90 92 94 96 98 100

Outflow (%)

Rec

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)

Goal

7Z6I

7Z6DOE

Baseline

Optimized

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Interaction of Normal Shock with Bleed

MFR = 0.919

MFR = 0.919

MFR = 0.919

MFR = 0.908

2.4%

0.8%2.1%

2.1%

% of capture flow

MFR = 0.892

MFR = 0.876

MFR = 0.859

MFR = 0.841

NASA “1507” Inlet (B1)

3.5%

4.9%

5.9%

6.9%

7.9%

1.7%

2.4%

3.2%

1.0%

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CFD Applications using Wind-US - Glenn Research Center · CFD Applications using Wind-US ... Supersonic Cruise Nozzle Validation case for NASA’s Next ... (DOE methods) – Off-design

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