Accession Number:

AD0671676

Title:

WIND TUNNEL INVESTIGATION OF ROLL RATE STABILITY DERIVATIVES - EXPLORATORY TESTS IN BTWT WITH A NEWLY DEVELOPED ROTATING STING SYSTEM,

Descriptive Note:

Corporate Author:

BOEING CO RENTON WASH COMMERCIAL AIRPLANE DIV

Personal Author(s):

• Smutny,P.
• Wilson,M. C.

Report Date:

1968-01-01

Pagination or Media Count:

41.0

Abstract:

Results of the first wind tunnel test to measure the rotary derivatives of a research model, using the developed rotary rig, are presented. Tests were conducted covering the Mach range from .16 to .85, angles of attack zero, 4 and 10 deg, and Reynolds number per foot from 900,000 to 3,500,000. The measured derivatives are compared with estimated values based on handbook method, linearized lifting surface theory and test data of a similar model. Author

Descriptors:

• *WIND TUNNEL MODELS
• *ROLL
• *AIRCRAFT MODELS
• ROLL
• STABILITY
• ROTATION
• MODEL TESTS
• SUBSONIC CHARACTERISTICS
• ANGLE OF ATTACK
• REYNOLDS NUMBER
• VELOCITY
• YAW

Subject Categories:

• Aerodynamics
• Aircraft
• Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE