• Blowdown, free-jet tunnel
• Utilizes nonvitiated air supply
  • 3MW graphite storage heater
• Provides:
  • True flight enthalpy test conditions
  • Altitude simulation
  • Air composition (Synthetic: GN2, GOx)
• Maximum Operating Conditions:
  • 3900°R maximum total temperature (mixed)
  • 1200 psig maximum total pressure
  • 222 lbm/sec Total Flow
  • Up to 120,000 ft altitude simulation
  • 5 minute run time (depending on operating conditions)
• 42 in. exit diameter nozzle
• 14 ft test section length available that can be expanded to 14 ft to accommodate longer test articles
• 8500 lbf thrust balance - single axis

Propellant Systems

• Gaseous H2
• Liquid hydrocarbons (JP7, JP10, etc.)
• Silane
• Upgrade possible for LOx and LH2
• LH2 system in standby

Control Systems

• PLC system - sequences facility systems
• Test Matrix Sequencer - sets run parameters

Data Systems

• Electronically Scanned Pressure System - ESP, 192 channels, x20/s
• Steady state data system - ESCORT: 528 channels, x1/s
• Dynamic data system - Concurrent Computer: "Masscomp System", 96 channels, 2MHz aggregate sampling
  

The HTF's operational altitude corridor

HTF Run Conditions
Nozzle	Mach 5	Mach 6	Mach 7
Stagnation Pressure, psia	410.0 70.5	1200.0 144.0	1200.0 430.0
Stagnation Temperature, R	2200 2420	2965 3310	3830 3900
Mass Flow, lbs/sec	189.0 30.9	222.0 25.4	104.0 36.2
Throat Diameter, in.	7.2 7.2	4.9 4.9	3.2 3.2
Exit Diameter, in.	42.0 42.0	42.0 42.0	42.0 42.0
Test Section	Mach 5	Mach 6	Mach 7
Static Pressure, psia	0.74 0.118	0.61 0.071	0.33 0.071
Static Temperature, R	384 428	390 451	412 451
Altitude, ft	68,000 108,000	72,000 120,000	93,000 120,000
Run Time, sec	103a 294b	42a 294b	90a 180c

a - Limited by maximum stagnantion temperature change of 200»F
b - Limited by steam availability at 150 psig
c - Limited by mixture and diffuser temperature limits