1

Integrity Service Excellence

Aerospace

Vehicles

Division

14 April 2015

Jon Tinapple Aerospace Vehicles Division

Aerospace Systems Directorate

Air Force Research Laboratory

Presented to the AFRL/NASA SBLI Technical Interchange Meeting, Tech Edge, Dayton

Program status and future plans for Supersonic Propulsion integration

research

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Briefing Content

•Motivation

•Technologies needed for Future Air

Dominance (FAD)

•Current road map

•Details of in-house efforts

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Motivation

Regain 4th gen. inlet aerodynamic performance while moving beyond 5th gen. survivability

Inlet Total Pressure Recovery vs. Mach Number

0.74

0.78

0.82

0.86

0.90

0.94

0.98

0.0 0.4 0.8 1.2 1.6 2.0 2.4Mach Number

PT

2/P

T0

F-14F-15F-16F-22

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Technologies Addressed by In-House research

In-House Technology Development:

• Bleed-less or low bleed shock wave boundary layer interaction flow control

• Fore body boundary layer thinning/diversion tech beyond F-35 bump

• Advanced compression systems to reduce cowl drag and achieve high pressure

recovery

• Subsonic diffuser flow control for aggressive diffusers downstream of normal shock

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2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024TRL 6 Need

Date

ASPIR II Inlet 4

Supersonic Propulsion Integration Research for Inlet Technologies (SPIRIT) In-House/Cooperative Testing

Yearly Total

Road Map Total

Intermediate Scale Full Flight Envelop with Rep Fore Body

Concept Development and small scale test with rep. fore body,

Large Scale validation with Rep Fore Body, Active Controls/Geometry

Assumes availability of 16S

5

4

6

FAD Propulsion Integration Inlet Systems

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Range of Experiments for Inlet Flow Control and Analysis

Correct flow throat to engine face, flight Re

Single shock interaction

Single shock with diffusion

Multiple shock system with diffusion (Generic inlet system) low Re

SOA inlet system

Previous Research Plan

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In-House Effort to Support FAD

• Supersonic tunnel is down for repairs. Next SWBLI model entry summer 2016• Developing in-house CFD capability to analysis flow fields and define effective

flow control configurations.• Design, fabricate and bench test Plasma flow control hardware using SBIR II.• Miniature scanning LDV probe system still under development at University of

Alabama

Use MAIBL hardware to develop external compression test fixture

Unprecedented model complexity for TGF

• Near term (FY15-16), working cooperatively with airframers to perform screening test of advanced compression systems, boundary layer diversion techniques and shock wave boundary layer interaction flow control.

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• Mid term (FY17-19), working cooperatively with airframers on subsonic diffuser flow control for aggressive offset diffusers .• Exhaust hardware being fabricated for facility.• Primary facility flow plug being designed.• Working on design of a new flow path that isMore relevant to external compression inlets. • Using NASA SUPIN code to develop initialFlow path

Add cowl spillage to direct connect rig to simulate external compression flow field. Construct aggressive offset diffusers

In-House Effort to Support FAD cont.

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• Improved understanding of corner flows in shock boundary layer interactions.• Current problems with SWBLI model related to inadequately controlled corner

flows.• Largest variation between modeling techniques show up as vastly different

corner flows.

• Expecting undesirables interactions between normal shock flow control and flow control for aggressive diffusion/curvature/shape change.

Basic Research Needed