Data reduction and procedures for conducting force tests in a 20 inch Mach 6 tunnel are described. A discussion of pretest and testing phases are included. Items that are to be checked during model design and construction are outlined as well as safety requirements, starting loads tests, instructions for data acquisition and model installation. Measurement of balance and model misalignment and instructions for calibrating the angle of attack screen are covered. Procedures for making reference pressure, attitude tare, and data runs are included. The 20 inch tunnel force program is examined, and a description of data recording system input and load contrast sheets is given. An appendix presents a description, operating characteristics, and Ma...
Checkout and data reduction procedures for acceptance test of sealed, absolute, gage, and differenti...
A description is given of each of the following Langley research and test facilities: 0.3-Meter Tran...
Experience with the Langley 0.3 meter transonic cryogenic tunnel, which is fan driven, indicated tha...
The operational characteristics and equipment associated with the Langley 16-foot transonic tunnel c...
A description and calibration is presented of the Langley 6- by 19-inch transonic tunnel which is a ...
The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility wit...
The Langley 14- by 22-Foot Subsonic Tunnel is used to test a large variety of aircraft and nonaircra...
Performance data are presented for this tunnel, which has a Mach number range from 2.0 to 3.5. The t...
The equations used by the 16 foot transonic tunnel in the data reduction programs are presented in e...
The equations used by the 16-Foot Transonic Wind Tunnel in the data reduction programs are presented...
The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunne...
Calibrations were obtained in the Langley 6 by 28-inch transonic tunnel with newly installed control...
A 20 ft vertical spin tunnel, a 30 by 60 ft tunnel, a 7 by 10 ft high speed tunnel, a 4 by 7 meter t...
The two test sections of the Langley Unitary Plan Wind Tunnel were calibrated over the operating Mac...
Report describes the development of the Langley annular transonic tunnel, a facility in which test M...
Checkout and data reduction procedures for acceptance test of sealed, absolute, gage, and differenti...
A description is given of each of the following Langley research and test facilities: 0.3-Meter Tran...
Experience with the Langley 0.3 meter transonic cryogenic tunnel, which is fan driven, indicated tha...
The operational characteristics and equipment associated with the Langley 16-foot transonic tunnel c...
A description and calibration is presented of the Langley 6- by 19-inch transonic tunnel which is a ...
The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility wit...
The Langley 14- by 22-Foot Subsonic Tunnel is used to test a large variety of aircraft and nonaircra...
Performance data are presented for this tunnel, which has a Mach number range from 2.0 to 3.5. The t...
The equations used by the 16 foot transonic tunnel in the data reduction programs are presented in e...
The equations used by the 16-Foot Transonic Wind Tunnel in the data reduction programs are presented...
The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunne...
Calibrations were obtained in the Langley 6 by 28-inch transonic tunnel with newly installed control...
A 20 ft vertical spin tunnel, a 30 by 60 ft tunnel, a 7 by 10 ft high speed tunnel, a 4 by 7 meter t...
The two test sections of the Langley Unitary Plan Wind Tunnel were calibrated over the operating Mac...
Report describes the development of the Langley annular transonic tunnel, a facility in which test M...
Checkout and data reduction procedures for acceptance test of sealed, absolute, gage, and differenti...
A description is given of each of the following Langley research and test facilities: 0.3-Meter Tran...
Experience with the Langley 0.3 meter transonic cryogenic tunnel, which is fan driven, indicated tha...