Specifications

Our Trisonic Wind Tunnel, one of the largest of it’s kind, is an intermittent blowdown facility with tandem subsonic / transonic and supersonic test sections.  This facility is used extensively in the development of military and commercial aircraft, providing testing services in the areas of aerodynamic forces, moments, and pressure loads; integrated propulsion systems; high speed flutter; flow field diagnostics; and shock interactions.

 

Tunnel Type:

Blowdown to Atmosphere
Test Section Types Tandem Solid & Porous Wall Sections

Test Section Size:

7 ft x 7ft x 9ft & 7 ft x 7 ft x 11 ft

Mach Range:

0.2 to 3.50

Unit Reynolds No:

2.5 to 20 million/foot

Operating Temp:

70OF ±10OF (stagnation)

Operating Pressure:

19 to 100 psia (stagnation)

Compressors:

10,000 hp, 34,500 SCFM @ 130psig

Air Storage:

214,000 ft3 (-30OF dewpoint)

Auxiliary HP Air:

470 ft3 @ 2,650 psi, up to 30 lb/sec. flow

Data Systems:

  Steady State
  Steady


179 channels, 56  samples/sec/channel

512 PSi pressure channels
Pressures:
  High Speed
  Very High Speed
44 channels, 500,000 s/sec aggregate
Modular, up to 1M samples/sec/ch.

Computing:

IBM Series 1 mainframe, networked PC's

Productivity:

2 to 4 blows per hour
 

 

Subsonic/Transonic Test Section
 

Test Section Walls:

19.7% Porosity

Mach Range:

0.1   to 1.3 standard

Calibrated to Mach 3.0

Max Reynolds Number:

10.5 million / ft @ M = 0.85

Operating Pressure:

19 to 37 psia

Run Times:

10 to 45 seconds

Flow Quality:

 

    Turbulence

1.1% P

    Noise @ M=0.85

150 db

    Flow Angularity

< 0.18 degrees

 

Supersonic Test Section
 

Test Section Walls:

Solid, Scliern windows

Mach Number:

1.4 to 3.5

Max Reynolds Number:

19 million / ft @ M = 2.4

Operating Pressure:

28 to 100 psia

Run Times:

5 to 25 sec

    Flow Angularity

< 0.18 degrees