Accession Number:

AD0736819

Title:

Results of Wind Tunnel Tests on a Flight Path Accelerometer at Mach Numbers from 0.2 to 3.0

Descriptive Note:

Final rept. 7 Jun-18 Aug 1971

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1972-02-01

Pagination or Media Count:

26.0

Abstract:

A program was conducted at the Arnold Engineering Development Center AEDC to design, fabricate, and test new full-scale angle-of-attack and sideslip vanes for the newly developed flight path accelerometer FPA to alleviate the dynamic stability problem of the previous vanes. The investigation was conducted in the von Karman Gas Dynamics Facility VKF Supersonic Wind Tunnel A and in the Propulsion Wind Tunnel Facility PWT Aerodynamic Wind Tunnel 4T. From dynamic stability tests of several vane configurations, the best performance vanes were selected and a position error calibration of Reynolds number rang based on boom diameter from 160,000 to 1,140,000. The angle of attack ranged from -3 to 24 deg. The selected vanes were dynamically stable over the entire Mach number range.

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE