Accession Number:

AD0672510

Title:

THE WIND TUNNEL FREE FLIGHT TESTING TECHNIQUE.

Descriptive Note:

Corporate Author:

BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD

Personal Author(s):

• Platou,Anders S.

Report Date:

1968-06-01

Pagination or Media Count:

31.0

Abstract:

The free flight wind tunnel technique has been used successfully to obtain aerodynamic coefficients on a variety of configurations with and without spin. High mass to moment of inertia ratio models are electroformed as 0.001 in. thick nickel shells with tungsten cores at the center of gravity CG. This permits wide CG variations and provides models which can withstand the high speed, high temperature flows. The model launcher is based on the principle of an inverted pea shooter. A 14 in. diameter tube in inserted into the aft portion of the model through the model base, and compressed air acting through the tube on the tungsten core propels the model forward. Spin can be imparted to the model with an air turbine just prior to launch. Cones have been launched with success up to 10,000 rpm, while high fineness ratio models have been launched at 40,000 rpm with moderate success. Author

Descriptors:

• (*WIND TUNNELS
• FREE FLIGHT MODELS)
• OPERATION
• LAUNCHING
• CONICAL BODIES
• TEST METHODS
• SPINNING(MOTION)
• OPTICAL EQUIPMENT
• WIND TUNNEL MODELS
• DATA PROCESSING
• AERODYNAMIC CHARACTERISTICS
• DRAG
• ROLL
• YAW
• SLENDER BODIES
• FORCE(MECHANICS)
• MAGNUS EFFECT
• SHOCK TUBES

Subject Categories:

• Test Facilities, Equipment and Methods
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE