Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory (MSL) Flexible Canopy Testing in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

5 HOLE PROBE CALLIBRATION FOR 10X10 FOOT SUPERSONIC WIND TUNNEL AND 8X6 FOOT SUPERSONIC WIND TUNNEL COMPARISON TEST

Parametric Inlet Model in 10x10 Wind Tunnel

Sonic Boom Model in the Abe Silverstein Supersonic Wind Tunnel (10x10)

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

Mars Science Laboratory, MSL Flexible Canopy Test in the Glenn Research Center, 10x10 Supersonic Wind Tunnel

ROCKET BASED COMBINED CYCLE - RBCC - RIG 3.1 MODEL INSTALLED IN 10X10 FOOT SUPERSONIC WIND TUNNEL TEST SECTION

ROCKET BASED COMBINED CYCLE - RBCC - RIG 3.1 MODEL INSTALLED IN 10X10 FOOT SUPERSONIC WIND TUNNEL TEST SECTION

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

ROCKET BASED COMBINED CYCLE - RBCC - RIG 3.1 MODEL INSTALLED IN 10X10 FOOT SUPERSONIC WIND TUNNEL TEST SECTION

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

DAN KOVACH WORKING ON THE ROCKET BASED COMBINED CYCLE RIG 3.1 MODEL IN THE 10X10 FOOT SUPERSONIC WIND TUNNEL

UNSTART PROGRAM - 10X10 FOOT SUPERSONIC WIND TUNNEL AS PART OF THE HIGH SPEED RESEARCH PROGRAM

Parametric Inlet Model in 10x10 Wind Tunnel

NASA Glenn/NASA Langley, Loads Comparison Test With 6 Component Force/Moment Balance and 1.7% High Speed Research, HSR Model 5. In the Glenn Research Center 10x10 Foot Supersonic Wind Tunnel, SWT

This test conducted in May 1988 shows what happens during launch if a space shuttle main engine fails. The test was conducted in the 10X10 supersonic wind tunnel at the John H. Glenn Research Center.

NASA GLENN/NASA LANGLEY LOADS COMPARISON TEST WITH 6 COMPONENT FORCE/MOMENT BALANCE AND 1.7% HIGH SPEED RESEARCH MODEL 5.l in the 10x10 supersonic wind tunnel

This test conducted in May 1988 shows what happens during launch if a space shuttle main engine fails. The test was conducted in the 10X10 supersonic wind tunnel at the John H. Glenn Research Center.

This test conducted in May 1988 shows what happens during launch if a space shuttle main engine fails. The test was conducted in the 10X10 supersonic wind tunnel at the John H. Glenn Research Center.

The flexwall section of NASA Glenn’s 10x10 supersonic wind tunnel is made up of two movable flexible steel sidewalls. These powerful hydraulic jacks move the walls in and out to control supersonic air speeds in the test section between Mach 2.0 and 3.5.

The 10- by 10-Foot Supersonic Wind Tunnel (10×10) is the largest and fastest wind tunnel facility at NASA’s Glenn Research Center and is specifically designed to test supersonic propulsion components from inlets and nozzles to full-scale jet and rocket engines.

Mars Science Laboratory (MSL) Flexible Canopy Test

Mars Science Laboratory (MSL) Flexible Canopy Test

SHUTTLE ENGINE OUT TEST done after the Space Shuttle Challenger disaster. This was part of the investigation after the Challenger accident

NASA GLENN/NASA LANGLEY LOADS COMPARISON TEST WITH 6 COMPONENT FORCE/MOMENT BALANCE AND 1.7% HIGH SPEED RESEARCH MODEL 5.

Mars Science Laboratory (MSL) Flexible Canopy Test

Mars Science Laboratory, MSL Flexible Canopy Test

Mars Science Laboratory, MSL Flexible Canopy Test

The NASA Fundamental Aeronautics Hypersonics project is focused on technologies for combined cycle, air-breathing propulsions systems to enable reusable launch systems for access to space. Turbine Based Combined Cycle (TBCC) propulsion systems offer specific impulse (Isp) improvements over rocket-based propulsion systems in the subsonic takeoff and re turn mission segments and offer improved safety. The potential to realize more aircraft-like operations with expanded launch site capability and reduced system maintenance are additional benefits.

The NASA Fundamental Aeronautics Hypersonics project is focused on technologies for combined cycle, air-breathing propulsions systems to enable reusable launch systems for access to space. Turbine Based Combined Cycle (TBCC) propulsion systems offer specific impulse (Isp) improvements over rocket-based propulsion systems in the subsonic takeoff and re turn mission segments and offer improved safety. The potential to realize more aircraft-like operations with expanded launch site capability and reduced system maintenance are additional benefits.