(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

(HWB) Hybrid Wing Body Aerodynamic Test in 14x22 12.3 Foot Span HWB Model as tested in the 14x22 Foot Subsonic Tennel Aerodynamic Test

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Helicopter active flow control tests in the 14X22 subsonic wind tunnel. Photos include preparation of the model before testing and the control room where testing is monitored and data collected

Osprey (UAV) Unmanned Aerial Vehicle ; flight vehicle test at 14x22 tunnel. Test number 605 from Eglin AFB. Take at 14x22 Subsonic Tunnel

Osprey (UAV) Unmanned Aerial Vehicle ; flight vehicle test at 14x22 tunnel. Test number 605 from Eglin AFB. Take at 14x22 Subsonic Tunnel

Osprey (UAV) Unmanned Aerial Vehicle ; flight vehicle test at 14x22 tunnel. Test number 605 from Eglin AFB. Take at 14x22 Subsonic Tunnel

Osprey (UAV) Unmanned Aerial Vehicle ; flight vehicle test at 14x22 tunnel. Test number 605 from Eglin AFB. Take at 14x22 Subsonic Tunnel

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section, building 1212C For more information go to NASA.gov article. April 3, 2019 "What is MADCAT?" Flexing Wings for Efficient Flight

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section, building 1212C For more information go to NASA.gov article. April 3, 2019 "What is MADCAT?" Flexing Wings for Efficient Flight.

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section, building 1212C. For more information go to NASA.gov article. April 3, 2019 " What is MADCAT? " Flexing Wings for Efficient Flight.

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section, building 1212C, Kenny Cheung from Ames Research Center in photograph. For more information go to NASA.gov article. April 3, 2019 "What is MADCAT?" Flexing Wings for Efficient Flight

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

Hybrid Wing Body Acoustic Test in 14x22 Tunnel ERA HWB Test -Acoustic

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

5.75% Scale Boeing BWB-0009G Model in NASA Langley 14x22 Foot Tunnel: Low speed aerodynamics test of BWB model with flow-thru nacelles in Langley 14x22 foot tunnel(test 617)

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Doublebubble MIT N+3 D8 1/11 Scale Model in the 14x22 Foot Subsonic Tunnel

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section. Interior of Structure. For more information go to NASA.gov article. April 3, 2019 "What is MADCAT?" Flexing Wings for Efficient Flight

Mission Adaptive Digital Composite Aerostructure Technologies (MADCAT) model in the 14x22 test section. Interior of structure. For more information go to NASA.gov article. April 3, 2019 "What is MADCAT?" Flexing Wings for Efficient Flight

The model of the Space Launch System for the Orion Space Capsule is being prepared for windtunnel test in the 14x22 Subsonic windtunnel at NASA Langley.

The model of the Space Launch System for the Orion Space Capsule is being prepared for windtunnel test in the 14x22 Subsonic windtunnel at NASA Langley.

The model of the Space Launch System for the Orion Space Capsule is being prepared for windtunnel test in the 14x22 Subsonic windtunnel at NASA Langley.

The model of the Space Launch System for the Orion Space Capsule is being prepared for windtunnel test in the 14x22 Subsonic windtunnel at NASA Langley.

The model of the Space Launch System for the Orion Space Capsule is being prepared for windtunnel test in the 14x22 Subsonic windtunnel at NASA Langley.

NASA employees Broderic J. Gonzalez, left, and David W. Shank, right, install pieces of a 7-foot wing model in preparation for testing in the 14-by-22-Foot Subsonic Wind Tunnel at NASA's Langley Research Center in Hampton, Virginia, in May 2025. The lessons learned from this testing will be shared with the public to support advanced air mobility aircraft development.

In May and June, NASA researchers tested a 7-foot wing model in the 14-by-22-Foot Subsonic Wind Tunnel at NASA’s Langley Research Center in Hampton, Virginia. The team collected data on critical propeller-wing interactions over the course of several weeks

NASA researcher Norman W. Schaeffler adjusts a propellor, which is part of a 7-foot wing model that was recently tested at NASA’s Langley Research Center in Hampton, Virginia. In May and June, NASA researchers tested the wing in the 14-by-22-Foot Subsonic Wind Tunnel to collect data on critical propeller-wing interactions. The lessons learned from this testing will be shared with the public to support advanced air mobility aircraft development.