Accession Number:

AD0321831

Title:

PRESSURE DISTRIBUTION TESTS ON A 60-DEG AND 70-DEG DELTA WING AT MACH NUMBERS 20 TO 22

Descriptive Note:

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Personal Author(s):

• WALLACE, A.R.
• SWAIN, W.N.

Report Date:

1961-02-01

Pagination or Media Count:

1.0

Abstract:

Pressure distribution tests were made on a 60-deg and a 70-deg delta wing with semicylindrical leading edges in Tunnel Hotshot 2 at mach numbers 20-22 and Reynolds numbers per foot of about 300,000. Angle of attack ranged from -10 to 60 deg. Author

Descriptors:

• *AERODYNAMIC CONFIGURATIONS
• *DELTA WINGS
• *HYPERSONIC WIND TUNNELS
• AERODYNAMIC CHARACTERISTICS
• HYPERSONIC FLOW
• MEASUREMENT
• MODEL TESTS
• PRESSURE
• SCHLIEREN PHOTOGRAPHY
• TRANSDUCERS

Subject Categories:

• Aircraft
• Test Facilities, Equipment and Methods
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE