Unitary and Continuous-Flow Hypersonic Tunnels
|Center:||Langley Research Center|
|Historic Eligibility:||National Register Eligible|
|Important Tests:||Military supersonic aircraft, early Space Shuttle development|
The Unitary Plan 4X4 Foot Supersonic Tunnel,one component of several tunnels at universities and at existing laboratories and at the Air Engineering Development Center, was approved under the Unitary Plan Act of 1949 and operational since 1955. The tunnel has two supersonic test sections that accommodate speeds from 1,000 to 3,000 miles per hour (Mach 1.5 to Mach 4.6). Developmental tests of almost every supersonic military aircraft and NASA spacecraft have been made in this tunnel. Typical testing at the facility include force and moment studies, discrete and global surface pressure measurements, and the application of various flow visualization techniques. Additionally, tests involving jet effects, dynamic stability, model deformation, global surface and off-body measurements and heat transfer have been conduced. Extensive experimental work on Space Shuttle was also conducted here, plus development of advanced concepts in supersonic civil and military aircraft. This facility has made critical contributions to the development, assessment, and optimization of advanced aerospace vehicle concepts through its decades of service.
The Mach 6 and 10 Tunnels are a part of the Langley Aerothermodynamics Laboratory. The Mach 10 Tunnel, also known as the Continuous-Flow Hypersonic Tunnel, was completed in 1957. The Hypersonic Flow Apparatus, or Mach 6 Tunnel, was completed two years later. In 1973, the Hypersonic Flow Apparatus housed in building 583 was dismantled and moved to building 1251.
The Mach 10 Tunnel has a 31-in test section with dry air as its medium. Dry air is also used as the test medium for the 15-in test section in the Mach 6 Tunnel. Today, tests ranging from heat-transfer studies to aerodynamics are completed in the tunnels.
The Continuous-Flow Hypersonic Tunnel was used to study problems spacecraft encounter as they leave or enter the atmosphere at very high speeds. The tunnel's equipment processes air to the extremely high pressures and temperatures needed to accelerate air to ten times the speed of sound. The large vacuum spheres were used to start the air flow. The facility contributed to the development of space programs from Apollo to the Space Shuttle.
In reviewing real property records and engineering drawing files, it is not clear when the division between 1251 and 1251A occurred. It appears from the drawing files that 1251A was used to denote the new test apparatus that was installed in existing rooms now known as 1251A. It is clear that these rooms were part of the original building (see proposed floor plan and 2012 floor plan in photos below).
[top] Shipyards Construction
This collection of photos was provided by the Northrop Grumman Shipbuilding-Newport News
[top] NACA/NASA Construction
[top] Facility Photos
[top] Mach 10 Tunnel
[top] Tests and Models
NASA made the decision to lease the Unitary Tunnel in preparation for future demolition. The following images were taken in October 2012 in preparation for the eventual demolition.
NACA/NASA and the National Unitary Wind Tunnel Plan, 1945-1965. R.D. Lanius, T.B Irvine, and E.A. Arrington. 2002. AIAA Meeting January 2002, Reno, NV.
[top] Technical Reports
Report Listing from December 1949 - October 1981. Complete listing of technical reports and papers produced from tests in Unitary Test Sections. Includes report number, title, author(s), and date. Most of these are available at http://ntrs.nasa.gov.
Description and Calibration of the Langley Unitary Plan Wind Tunnel. Charlie M. Jackosn, Jr., William A. Corlett, and William J. Monta. 1981. TP 1905.
Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 deg to 15 deg. Robert L. Stallings, Jr. and Dorothy T. Howell. 1969. TN D-5392.
Drag reduction due to gas injection through various discrete slots on a three-dimensional wing at Mach 2.01. Russel B. Sorrells III, K. R. Czarnecki, and Lorraine F. Satchell. 1969 TN D-5307.
Effects of additional revisions on the aerodynamic characteristics of a target drone vehicle at Mach numbers from 1.70 to 4.63. COORD no. AF-AM-827. A. B. Blair, Jr. and Dorothy H. Tudor. 1970. TM X-1961.
Sonic-boom characteristics in the extreme near field of a complex airplane model at mach numbers of 1.5, 1.8, and 2.5. Odell A. Morris, Milton Lamb, Harry W. Carlson. 1970. TN D-5755.
Effects of nose bluntness on aerodynamic characteristics of cruciform-finned missile configuration at mach 1.50 to 2.86. Lloyd S. Jernell. 1970. TM X-2031.
Aerodynamic interference effects on half-cone bodies with thin wings at mach 10.03. James C. Townsend. 1970. TN D-5898.
Experimental wake survey behind a 120 deg-included-angle cone at angles of attack of 0 deg and 5 deg, mach numbers from 1.60 to 3.95, and longitudinal stations varying from 1.0 to 8.39 body diameters. Clarence A. Brown, Jr., James F. Campbell, Dorothy H. Tudor. 1971. TM X-2139.
Theoretical pressure distributions over arbitrarily shaped periodic waves in subsonic compressible flow and comparison with experiment. K. R. Czarnecki, Mary W. Jackson. 1970. TN D-5984.
Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds. William A. Cassels, James F. Campbell. 1970. TN D-6063.
Supersonic aerodynamic characteristics of a rocket-vehicle model with low-aspect-ratio wing and tail surfaces. Ernald B. Graves. 1971. TM X-2159.
A wind-tunnel investigation of sonic-boom pressure distributions of bodies of revolution at mach 2.96, 3.83, and 4.63. Barrett L. Shrout, Robert J. Mack, Samuel M. Dollyhigh. 1971. TN D-6195.
Wind-tunnel investigation of sonic-boom characteristics of two simple wing models at mach numbers from 2.3 to 4.63. David S. Miller, Odell A. Morris, Harry W. Carlson. 1971. TN D-6201.
Aerodynamic characteristics of wing-body configurations of hypersonic cruise aircraft at mach 2.30 to 4.63 Lloyd S. Jernell. 1971. TM X-2287.
Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds. Lloyd S. Jernell. 1971. TN D-6480.
Longitudinal Aerodynamic characteristics at mach 1.50 to 4.63 of a missile model employing various canards and a trailing-edge flap control. Charles D. Trescot, Jr. 1971. TM X-2367.
A method for calculating the aerodynamic loading on wing-body combinations at small angles of attack in supersonic flow. Charlie M. Jackson, Jr., Wallace C. Sawyer. 1971. TN D-6441.
An improved method for calculating supersonic pressure fields about bodies of revolution. Robert J. Mack. 1971. TN D-6508.
Experimental wake survey behind Viking '75 entry vehicle at angles of attack of 0 deg and 5 deg, mach numbers from 1.60 to 3.95, and longitudinal stations from 1.0 to 8.39 body diameters. Clarence A. Brown, Jr., James F. Campbell. Dorothy H. Tudor. 1971. TM X-2312.
Experimental wake survey behind a 140 deg-included-angle cone at angles of attack of 0 deg and 5 deg, mach numbers from 1.60 to 3.95, and longitudinal stations varying from 1.0 to 8.39 body diameters. Clarence A. Brown, Jr., James F. Campbell. 1971. TM X-2409.
Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated. Ernald B. Graves. 1972. TM X-2531.
- Static longitudinal aerodynamic characterisitcs of close-coupled wing-canard configurations at mach numbers from 1.60 to 2.86. Samuel M. Dollyhigh. TN D-6597.
- Pitot-probe displacement in a supersonic turbulent boundary layer. Jerry M. Allen. TN D-6759.
- Some effects of external stores on the static stability of fighter airplanes. Morris Leroy Spearman. TN D-6775.
- Aerodynamic characteristics of a 60 deg swept delta-wing space shuttle orbiter at mach numbers of 2.50, 3.90, and 4.60. Ernald B. Graves. TM X-2561.
Effect of nose shape and tail length on supersonic stability characterisitics of a projectile. Wallace C. Sawyer, Ida K. Collins. 1973. TM X-2381.
Drag characteristics of circular cylinders in a laminar boundary layer at supersonic free-stream velocities. Robert L. Stallings, Jr., Milton Lamb, Dorothy T. Howell. 1973. TN D-7369.
Comparisons of two-dimensional cshock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds. Lloyd S. Jernell. 1974. TN D-7583.
Effects of reynolds number and model support on the supersonic aerodynamic characterisitics of a 140 deg-included-angle cone. Charles D. Trescot, Jr., Clarence A. Brown, Jr., Dorothy T. Howell. 1974. TM X-3019.
Stability and control characteristics at Mach numbers from 0.20 to 4.63 of a cruciform air-to-air missile with triangular canard controls and a trapezoidal wing. Ernald B. Graves, Roger H. Fournier. 1974. TM X-3070.
Stability and control characteristics of a monoplane missile with large delta wings and various tail controls at Mach 1.90 to 2.86. Lloyd S. Jernell. 1974. TM X-71984.
Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities. Milton Lamb, Robert L. Stallings, Jr. 1972. TN D-7812.
Numerical methods for the design and analysis of wings at supersonic speeds. Harry W. Calson, David S. Miller. 1974. TN D-7712.
Minimization of sonic-boom parameters in real and isothermal atmospheres. Christine M. Darden. 1975. TN D-7842.
A generalized theory for the design of contraction cones and other low speed ducts. Raymond L. Barger, John T. Bowen. 1972. TN D-6962.
Evaluation of compressible-flow Preston tube calibrations. Jerry M. Allen. 1973. TN D-7190.
Application of sonic-boom minimization concepts in supersonic transport design. Harry W. Carlson, Raymond L. Barger, Robert J. Mack. 1973. TN D-7218.
- Streamline curvature design procedure for subsonic and transonic ducts Raymond L. Barger. TN D-7368.
On the use of thick-airfoil theory to design airfoil families in which thickness and lift are varied independently. Raymond L. Barger. TN D-7579.
Effects of Mach number on pitot-probe displacement in a turbulent boundary layer. Jerry M. Allen. TN D-7466.
Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage. Samuel M. Dollyhigh. TM X-3078.
A streamline curvature method for design of supercritical and subcritical airfoils. Raymond L. Barger, Cuyler W. Brooks, Jr. TN D-7770.
A modified Theodorsen epsilon-function airfoil design procedure. Raymond L. Barger. TN D-7741.
Procedures for the design of low-pitching-moment airfoils. Raymond L. Barger. TN D-7982.
Flight transition data for angles of attack at Mach 22 with correlations of the data. Charles B. Johnson. Christine M. Darden. TM X-3235.
Investigation of the static lift capability of a low-aspect-ratio wing operating in a powered ground-effect mode. Jarrett K. Huffman. Charlie M. Jackson, Jr. TM X-3031.
Aerodynamic Analyses Requiring Advanced Computers, part 2. Raymond L. Barger. Cuyler W. Brooks, Jr. SP-347.
Second-order small-disturbance solutions for hypersonic flow over power-law bodies. James C. Townsend. TN D-7973.
Aerodynamic characteristics of a hypersonic research airplane concept having a 70 degree swept double delta wing at Mach numbers from 1.50 to 2.86. Jim A. Penland. Roger H. Fournier. Don C. Marcum, Jr. TN D-8065.
A numerical technique for analysis of wave drag at lifting conditions. Roy V. Harris, Jr. TN D-3586.
Experimental flow properties in the wake of a 120 deg cone at Mach number 2.20. James F. Campbell. Josephine W. Grow. TN D-5365.
Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4. John B. Peterson, Jr. TN D-5523.
Supersonic lifting capabilities of large-angle cones. James F. Campbell. Dorothy T. Howell. TN D-5499.
Charts for interpolation of local skin friction from experimental turbulent velocity profiles. Jerry M. Allen. Dorothy H. Tudor. SP-3048.
A numerical method for evaluation and utilization of supersonic nacelle-wing interference. Robert J. Mack. TN D-5057.
Experimental heat-transfer distributions on a blunt lifting body at Mach 3.71. Robert J. Stallings Jr. Robert L. Wright. Ida K. Collins. TN D-5616.
A study of the application of heat or force fields to the sonic-boom-minimization problem. David S. Miller. Harry W. Carlson. TN D-5582.
Aeronautical characteristics of an oblate spheroid and a sphere at Mach numbers from 1.70 to 10.49. Lloyd S. Jernell. TN D-5600.
A method for determining surface pressures on blunt bodies of revolution at small angles of attack in supersonic flow. Charlie M. Jackson, Jr. Wallace C. Sawyer. Rudeen S. Smith. TN D-4865.
Pressure distributions on 140 deg, 160 deg, and 180 deg cones at Mach numbers from 2.30 to 4.63 and angles of attack from 0 deg to 20 deg. James F. Campbell. Dorothy H. Tudor. TN D-5204.
Experimental pressure distributions on a 120 deg cone at Mach numbers from 2.96 to 4.63 and angles of attack from 0 deg to 20 deg. Robert J. Stallings, Jr. Dorothy H. Tudor. TN D-5054.
Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71. W. Douglas Morris. Lana M. Couch. TN D-4494.
Aerodynamic characteristics of two blunt, half-cone wedge entry configurations at Mach numbers from 2.30 to 4.63. Gerald V. Foster. TM X-1621.
Supersonic aerodynamics of large-angle cones. James F. Campbell. Dorothy T. Howell. TN D-4719.
Drag due to two-dimensional surface roughness in a turbulent boundary layer at Mach 3 with and without heat transfer. William J. Monta. K. R. Czarnecki. William D. Deveikis. TN D-4746.
Effects of nose shape and fin geometry on static stability of a high-fineness-ratio sounding rocket. Dennis E. Fuller. TM X-1661.
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of attack to 180 deg. Lloyd S. Jernell. TM X-1658.
Aerodynamic characteristics of a parasol-wing-body combination utilizing favorable lift interference at Mach numbers from 3.00 to 4.63. Odell A. Morris. Robert J. Mack. TN D-4855.