Accession Number:

AD0457591

Title:

EXPERIMENTAL INVESTIGATION OF THE IMPACT PROBE METHOD FOR DETERMINING LOCAL SKIN FRICTION IN THE PRESENCE OF AN ADVERSE PRESSURE GRADIENT FOR A RANGE OF MACH NUMBERS FROM 1.70 TO 2.75.

Descriptive Note:

Technical rept.,

Corporate Author:

TEXAS UNIV AT AUSTIN DEFENSE RESEARCH LAB

Personal Author(s):

• Hill, Oliver

Report Date:

1963-01-01

Pagination or Media Count:

1.0

Abstract:

This thesis presents the results of an experimental program to determine the feasibility of using a surface impact probe to measure values of local skin friction in a turbulent boundary layer over a range of Mach Numbers and pressure gradients. This work is an extension of previous work on adverse pressure gradients which was done at a nominal Mach Number of 2.0. The present investigation was conducted on an adiabatic flat surface which formed the test-section floor of a variable Mach Number supersonic wind tunnel. The Mach Numbers ranged from 1.70 to 2.75 with adverse pressure gradients of zero to 1.57 psiin. Author

Descriptors:

• *PITOT TUBES
• *SKIN(ANATOMY)
• FRICTION
• FRICTION
• SHEAR STRESSES
• PRESSURE
• SUPERSONIC FLOW
• TURBULENT BOUNDARY LAYER
• FLAT PLATE MODELS
• WIND TUNNEL MODELS
• MODEL TESTS
• DRAG
• ADIABATIC GAS FLOW
• COMPRESSIBLE FLOW
• MATHEMATICAL ANALYSIS
• EQUATIONS
• MEASUREMENT
• ERRORS
• EXPERIMENTAL DATA
• TABLES(DATA)
• GRAPHICS
• FEASIBILITY STUDIES
• SURFACE PROPERTIES

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE