	Facilities of the NASA Langley Scramjet Test Complex

Graphical Depiction of Scramjet Test Facility Mach # vs. Altitude Operational Envelopes

Wind Tunnel Enterprise (WTE) Hypersonic Airbreathing Propulsion Facilities Summary Page

Facility		Primary Use	Simulated Flight Mach Number	Nozzle Exit Mach Number	Nozzle Exit Size (in.)	Test Section Dimensions (ft.)
Direct-Connect Supersonic Combustion Test Facility (HAPB DCSCTF Site) (WTE DCSCTF Site) (WTE Brochure)		Combustor Tests	4.0 to 7.5	2.0 2.7	1.52 x 3.46 1.50 x 6.69	N/A
Combustion- Heated Scramjet Test Facility (WTE-CHSTF) *(WTE Brochure)*		Engine Tests	3.5 to 5.0 4.7 to 6.0	3.5 4.7	13.26 x 13.26	2.5 W x 3.5 H x 8 L
Arc-Heated Scramjet Test Facility (WTE-AHSTF) *(WTE Brochure)*		Engine Tests	4.7 to 5.5 6.0 to 8.0	4.7 6.0	11.17 x 11.17 10.89 x 10.89	4 dia. x 11 L
8-ft. High Temperature Tunnel (WTE-8-Ft HTT) (WTE Brochure)		Engine Tests	4.0 5.0 6.8	4.0 5.0 6.8	96 dia.	8 dia. x 12 L
Hypersonic Pulse Facility (HYPULSE)	SETb	Combustor Tests	12.0 14.0 15.0 17.0	4.7 4.8 or 6.2 5.0 7.2	6 dia. 6 or 12 6 6	4 dia. x 30 L
Hypersonic Pulse Facility (HYPULSE)	RST/SETn	Engine Tests	7 10	7.2 6.4	26.25 dia.	7 dia. x 20 L

Note: WTE is NASA Langley's Wind Tunnel Enterprise, a network of service producers, customers, and infrastructure investors whose mission is to provide reliable, accurate research information to the aeronautical community in a timely manner. This is accomplished by setting goals which focus on increasing productivity, cost effective operations, technical support that adds value, and the development of new facility capability and test techniques.

Related Publications

R. W. Guy, R. C. Rogers, R. L. Puster, K. E. Rock and G. L. Diskin, The NASA Langley Scramjet Test Complex, AIAA Paper 96-3243, 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 1-3, 1996, Lake Buena Vista, Florida.

AHSTF

Langley Facility for Tests at Mach 7 of Subscale, Hydrogen-burning, Airframe-integratable, Scramjet Models, Boatright, W. B., Sabol, A. P., Sebacher, D. I., Pinckney, S. Z., and Guy, R. W., AIAA-1976-11 AIAA 14th Aerospace Sciences Meeting, January 26-28, 1976, Washington, D.C.

Operating Characteristics of the Langley Mach 7 Scramjet Test Facility, Guy, R.W., Torrence, M.G., Sabol, A.P. and Mueller, J. N. NASA TM-81929, March, 1981.

Increased Capabilities of the Langley Mach 7 Scramjet Test Facility, Thomas, S.R. and Guy, R.W., AIAA-82-1240, AIAA/SAE/ASME 18th Joint Propulsion Conference, June 21-23, 1982, Cleveland, Ohio.

Expanded Operational Capabilities of the Langley Mach 7 Scramjet Test Facility, Thomas, S.R. and Guy, R.W., NASA TP- 2186, October 1983.

Test Flow Calibration Study of the Langley Arc-Heated Scramjet Test Facility, Thomas, S.R., Voland, R.T. and Guy, R.W., AIAA-87-2165, AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference June 29-July 2, 1987, San Diego, California.

CFD Simulation of Square Cross-Section, Contoured Nozzle Flows: Comparison With Data, Ostrander, M.J., Thomas, S.R., Voland, R.T., Guy, R.W. and Srinivassan, S., AIAA 1989-45, 27th Aerospace Sciences Meeting, January 9-12, 1989, Reno, Nevada.

1998 Calibration of the Mach 4.7 and Mach 6 Arc-Heated Scramjet Test Facility Nozzles, Witte, D.W., Irby, R.G., Auslender, A.H. and Rock, K.E., NASA/TM-2004-213250, August, 2004.

Analysis and Design of Rectangular-Cross-Section Nozzles for Scramjet Engine Testing, Gaffney, R.L. Jr. and Korte, J.J, AIAA 2004-1137, 42nd AIAA Aerospace Sciences Meeting and Exhibit, January 5-8, 2004, Reno, Nevada.

CHSTF

Design, Tests, and Verification of a Diffuser System for a Mach 4 Scramjet Test Facility, Andrews Jr., E.H and Mackley, E.H., AIAA-1978-771(revised) AIAA 10th Aerodynamic Testing Conference, April 19-21, 1978, San Diego, California.

Design, Tests, and Verification of a Diffuser System for a Mach 4 Scramjet Test Facility, Andrews Jr., E.H and Mackley, E.H., AIAA Journal of Aircraft, Vol. 16, No. 10, October, 1979, pp641-642.

Langley Mach 4 Scramjet Test Facility, Andrews Jr., E.H., Torrance, M.G., Anderson, G.Y., Northam, G.B, and Mackley, E.H., NASA TM-86277, February, 1985.

A Subsonic to Mach 5.5 Subscale Engine Test Facility, Andrews, Jr, E.H., AIAA-87-2052, AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference, June 29-July 2, 1987, San Diego, California.

Enhanced Capability of the Combustion-Heated Scramjet Test Facility, Rock, K.E., Andrews Jr., E.H., and Eggers, J.M., AIAA 91-2502, AIAA/SAE/ASME/ASEE 27th Joint Propulsion Conference, June 24-26, 1991, Sacramento, California.

DCSCTF

8-FT HTT

Modification to the Langley 8-Foot High Temperature Tunnel for Hypersonic Propulsion Testing, Reubush, D.E. and Puster, R.L., AIAA 1987-1887, AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference, June 29-July 2, 1987, San Diego, California.

Calibration of the Langley 8-Foot High Temperature Tunnel for Hypersonic Airbreathing Propulsion Testing, Huebner, L.D., Rock, K.E., Voland, R.T. and Wieting, A.R., AIAA 96-2197, 19th AIAA Advanced Measurement and Ground Testing Technology Conference, June 17-20, 1996 / New Orleans, LA.

Test Capabilities and Recent Experiences in the NASA Langley 8-foot High Temperature Tunnel, Hodge, J.S. and Harvin, S.F., AIAA 2000-2646, AIAA 21stAerodynamic Measurement Technology and Ground Testing Conference, June 19-22, 2000, Denver, CO.

The Design of a High-Q, MACH-5 Nozzle for the Langley 8-Foot HTT, Gaffey, R.L., Jr., Stewart, B.K. and Harvin, S.F., AIAA Paper 2006-2954, 25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, June 5-8, 2006, San Francisco, California.

Test Capability Enhancements to the NASA Langley 8-Foot High Temperature Tunnel, Harvin, S.F., Cabell, K.F., Gallimore, S.D. and Mekkes, G.L., JANNAF 41st Combustion 29th Airbreathing Propulsion 23rd Propulsion Systems Hazards Joint Subcommittee Meeting, December 4-8, 2006, San Diego, California.

Design of a Mach-3 Nozzle for TBCC Testing in the NASA LaRC 8-ft High Temperature Tunnel,Gaffney, R. L., Jr.; Norris, A. T., AIAA Paper-2008-3703, 26th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 23-26 Jun. 2008, Seattle, Washington.

Additional HAPB Experimental Facilities

Facility		Primary Purpose
Mach 4 Blow-down Facility *(M4BDF)*		Inlet Screening and Testing
Mixing Studies Facility		Mixing Enhancement, Fuel Injector Studies, Drag Reduction, Code Validation Studies
Nonintrusive Diagnostics Labs		CARS, RELIEF, PDV
Basic Combustion Laboratory		Opposed Jet Burner Studies - Flameholding -Vitiation Effects Use And Evaluate Combustion Diagnostic Techniques
Propulsion Instrumentation Shock Tube Laboratory *(PISTL)*		Instrumentation For Pulse Facilities, Diaphragm Dynamics, Pulse Facility Phenomena

Additional Refererence Documents

Wind-Tunnel Model Systems Criteria - LAPR 1710.15, This procedure and guideline sets forth criteria for the design, analysis, quality assurance, and documentation of wind-tunnel model systems to be tested at the Langley Research Center (LaRC) and is incorporated into the LaRC Safety Manual, "Facility Safety Standards," section.

Langley Research Center Pressure Systems Handbook - LAPR 1710.40, This Langley Procedural Requirement (LPR) implements the requirements of NASA NPD 8710.5, “NASA Safety Policy for Pressure Vessels and Pressurized Systems,” and is part of the Langley Management System. It establishes requirements and standards for pressurized systems within the framework of Langley Research Center safety policies and constraints. It provides a basis for safety and uniformity in the design, procurement, fabrication, and use of pressure vessels, piping, and associated equipment.