Primarily for indigenous development testing
Testing requirements of R & D organizations and other
industries
For both aeronautics & non aeronautical applications

Types of tests performed:
Steady and Unsteady force & moment measurements
 Steady and fluctuating pressure measurements
 Wind Engineering
 Flow visualization
 Flow diagnostic tests

Special tests:
Ground effect measurements
Component loads measurements
 Efflux trails for ship models
Stores release (gravity drop)

Type of Tunnel:  Closed Circuit, Closed jet, continuous flow subsonic wind tunnel
Test Section size and shape: 2.74 m x 1.83 m, octagonal
Speed range/ Mach number range: 10 – 55 m/s
Reynolds number range (per m): 0.63 – 3.46 millions
Free stream turbulence level (If low speed tunnel): 2%
Test Control Parameters:
 Pitch angle (normal testing):–18 degrees to 42
 Yaw angle (normal testing): – 28 degrees to 28
Typical test duration : 15 min
High angle of attack testing: -90 degrees 

Data Acquisition System:
Industrial PC based DAS making use of NI simultaneous sampling 16 bit ADC.
NI DAQ and Lab View platform for Acquisition
In house developed soft ware for acquisition, processing and presentation

Special test rigs and test techniques developed:
High angles of attack rig
Smoke trials at very low speeds
Gravity release technique
Oil dot technique
Ejector developments

Milestones achieved:
More than 37 projects and 51 models tested since inceptions
Completed all the low speed test requirements for major  projects like ALH, IJT, LCH, P-17, P-28, AMCA, HTT-40, FGFA
 

The Director  
Indian Institute of Space Science and Technology
Valiamala P O,
Thiruvananthapuram – 695547
Phone: +91 (471) 2568452, 2568600 
Fax: +91 (471) 2568462 
Email: admin@iist.ac.in
Website:  http://www.iist.ac.in/