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Inlets and Nozzles

NASA is advancing inlets and nozzles for aircraft engines and aerospace applications through research supporting commercial, military aircraft, and space propulsion systems.

A metallic aircraft model mounted on a support inside a blue wind tunnel, surrounded by perforated walls and floor for aerodynamic testing.

Overview

Our aircraft engine inlet and nozzle researchers maintain and operate several test facilities at NASA’s Glenn Research Center in Cleveland where we perform the following tasks:

  • Measure the performance of advanced inlets and nozzles designs
  • Study flow control concepts for improved inlets and nozzles performance
  • Provide inlet/fan interaction data
  • Investigate nozzle aeroacoustic issues
  • Understand fundamental flow physics issues relevant to inlets and nozzles flows
  • Produce detailed test data for validation of computational fluid dynamics (CFD) codes

Our researchers also develop, maintain, support, and apply several computational fluid dynamics (CFD) codes, which are used for the following:

  • Design advanced inlets and nozzles
  • Predict inlets and nozzles performance
  • Model flow control concepts
  • Model inlet/fan interaction
  • Understand aeroacoustic phenomena
  • Study fundamental flow problems
  • Develop and evaluate advanced prediction methods for turbulent flow physics, with a focus on propulsion system components

Advancing Flight Technology Through Research, Modeling, and Demonstration

NASA Glenn conducts fundamental physics-based experiments and develops validated models to advance the understanding of inlet and nozzle aerospace propulsion performance. This includes rigorous component-level testing to characterize flow behavior and validate predictive tools under realistic operating conditions. Leveraging advanced design and analysis software—along with proven expertise in flight demonstrations such as the X-59—NASA Glenn enables high-fidelity simulation, system integration, and real-world validation of next-generation aerospace technologies.

A color map plot showing velocity difference (u−U)/ΔU across x (mm) and y (mm) axes, with color bar from blue (0) to red (1). The flow pattern varies along staggered measurement sections. Inset text: Mₑ = 0.19.

Fundamental Physics Experiments

Fundamental physics experiments increase our understanding of more complex problems and provide important data for improving and validating physical models.

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Color diagram showing Mach number distribution around a sloped object in a wind tunnel. The flow, labeled M = 2.46, forms shock waves and expansion fans. Axes are labeled in inches; a color bar indicates Mach values from 0 to 2.5.

Physics Modeling and Validation

Improvements in physical modeling and the validation of these methods are critical to advancing numerical simulation capabilities.

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• Rendered 3D diagrams of supersonic jet engine inlets, with internal structures highlighted in yellow, showing side, rear, and angled views of various aerodynamic designs.

Design and Analysis Software

A range of advanced software tools is used to support the design, analysis, and testing of inlets and nozzles for aerospace propulsion systems.

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A metallic aircraft model mounted on a support inside a blue wind tunnel, surrounded by perforated walls and floor for aerodynamic testing.

Support of Flight Demonstration Projects

Computational fluid dynamics, wind tunnel tests, real-time displays, and system integration support X-59 supersonic flight.

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Facilities

Our inlet and nozzle researchers maintain and operate several test facilities used to support the following activities:

  • Measuring the performance of advanced inlet and nozzle designs
  • Studying flow control concepts to improve inlet and nozzle performance
  • Providing inlet/fan interaction data
  • Investigating nozzle aeroacoustic phenomena
  • Advancing understanding of fundamental flow physics relevant to inlet and nozzle flows
  • Producing detailed test data for the validation of computational fluid dynamics (CFD) codes

Exhaust Nozzle Plume Effects on Sonic Boom Hardware

1 x 1 Supersonic Wind Tunnel

Conducts fundamental research in supersonic and hypersonic flows, vehicle-focused studies, and benchmark experiments for CFD code validation.

The 10x10 Supersonic Wind Tunnel flex wall system.

10 x 10 Abe Silverstein Supersonic Wind Tunnel

Specifically designed to test supersonic propulsion components from inlets and nozzles to full-scale jet and rocket engines.

A man wearing glasses operates scientific equipment in a laboratory, adjusting a metal component under a machine surrounded by metal columns and electronic devices.

15 x 15 Supersonic Wind Tunnel

Continuous flow facility is used to study fundamental flow physics and serve as a test bed for instrumentation.

A man wearing glasses operates scientific equipment in a laboratory, adjusting a metal component under a machine surrounded by metal columns and electronic devices.

20 x 30 Low Speed Wind Tunnel

Self-contained test rig for studying flow separation and 2-D shear layers. Features an 80-inch test section and variable-speed drive enabling airflow up to 15 m/s.

Boeing Quiet Experimental Validation Concept, QEV

8 x 6 Supersonic Wind Tunnel

Operates either in an aerodynamic closed-loop cycle, testing aerodynamic performance models, or in a propulsion open-loop cycle that tests live fuel-burning engines and models.

Advanced Ducted Propulsor (ADP) Fan Commissioning Test (side view) in the 9x15 Low-Speed Wind Tunnel.

9 x 15 Low Speed Wind Tunnel

The world’s most used low-speed propulsion acoustic facility and the only U.S. site that continuously simulates takeoff, approach, and landing in a subsonic environment.

A man wearing glasses operates scientific equipment in a laboratory, adjusting a metal component under a machine surrounded by metal columns and electronic devices.

Advanced Nozzle Test Facility

Tests advanced nozzles with heated airflows and altitude simulation up to 48,000 feet. Supports CFD validation and performance testing with modular, dual-flow air supply.

Nozzle Acoustic Test Rig (NATR) in the Aero-Acoustic Propulsion Laboratory

Aero-Acoustic Propulsion Laboratory

World-class facility with over 20 years of experience in aircraft propulsion noise-reduction and performance research, offering advanced acoustic testing services.

A man wearing glasses operates scientific equipment in a laboratory, adjusting a metal component under a machine surrounded by metal columns and electronic devices.

Free Jet Facility

Conducts experiments to develop fundamental understanding of the jet mixing process and to increase jet mixing efficiency.

Direct connect configuration of the interior of the Hypersonic Tunnel Facility.

Hypersonic Tunnel Facility

A hypersonic (Mach 5, 6, and 7) blowdown, non-vitiated free jet facility that tests large-scale hypersonic air-breathing propulsion systems.

A man wearing glasses operates scientific equipment in a laboratory, adjusting a metal component under a machine surrounded by metal columns and electronic devices.

Internal Fluid Mechanics Facility

A hypersonic (Mach 5, 6, and 7) blowdown, non-vitiated free jet facility that tests large-scale hypersonic air-breathing propulsion systems.

Ice Measurement Probes in the Propulsion Systems Laboratory

Propulsion Systems Laboratory

Provides true flight simulation for experimental research on air-breathing propulsion systems and can simulate clouds of ice crystals and liquid water droplets.