Subsonic, Transonic Wind Tunnel Testing


Calspan’s Subsonic, Transonic Wind Tunnel is the only independently owned and operated wind tunnel in the United States. Our staff is known for its flexibility and responsiveness to our customer’s needs for all wind tunnel testing. Customers appreciate this approach, as it enables them in real time, to refine test programs that support the various phases of an aircraft’s development.  This efficiency promotes less time required to down select and perform design optimization. Calspan also offers to its customers the management of model design and fabrication, prior to program commencement, through our Calspan Systems team.

Our Subsonic, Transonic Wind Tunnel facility is fully compliant with the JAFAN 6/9 security specification and is approved to support testing at the Secret-SAP level (when required). Customer models, data, and related program information are all handled in a strictly proprietary manner. This protects the sensitive nature of the work we conduct on behalf of our customers. Additionally, all Calspan Wind Tunnel staff (including support staff) carry U.S. government clearances at the Secret level or above. Test and Calibration Areas, Model Buildup Rooms, Control Room, Data Reduction Room, and Customer Processing Rooms can all be secured to allow for the processing of classified information.

Our Subsonic, Transonic Wind Tunnel Services


The Markets We Serve and Data Processing

Calspan has developed specialized tests, instrumentation, and data acquisition systems to evaluate the performance of Military Aircraft + Weapons, Space Access Vehicles, Ram Air Turbines and Passenger + Commercial Aircraft. Throughout these test programs, our wind tunnel experts provide customers with high-quality data that is specifically formatted to each customer’s requirements.

Facility Details

Calspan’s Subsonic, Transonic Wind Tunnel is a continuous flow, variable density, closed-circuit facility with an 8 foot x 8 foot test section. Test conditions are set via independent control of Mach number and one other pressure-dependent variable for constant Reynolds number, static pressure, dynamic pressure, or total pressure operations. Other details about our test facilities include:
  • Maximum Mach Number of 1.30
  • Stagnation Pressures of 0.25 to 3.25 Atmospheres
  • Reynolds Numbers up to 4.5 x 10^6 per foot (Conventional)
  • Reynolds Numbers up to 10.5 x 10^6 per foot (Ejectors)