Accession Number:

ADA089851

Title:

Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and its Effects on Aircraft Motion

Descriptive Note:

Final rept. 1 Oct 1978-31 Oct 1979

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1980-09-01

Pagination or Media Count:

95.0

Abstract:

A wind tunnel test program and an analytical study were conducted to investigate aerodynamic hysteresis phenomena on the F-4 aircraft. The wind tunnel test was conducted in the Arnold Engineering Development Center AEDC aerodynamic Wind Tunnel 4T to investigate the source of aerodynamic hysteresis in static aerodynamic data. The wind tunnel test also provided data that were used in a motion simulation study of the effect of hysteresis on predicted aircraft motion. Static longitudinal lateral directional force and moment data and wing pressure data were obtained on a 0.5-scale model without pylons or external stores with various simulated leading-edge slats. These data include the effects of Mach number, angle of attack, model movement, and time dependence on the aerodynamic hysteresis characteristics. Data are presented for the Mach number range from 0.7 to 0.95 at angles of attack from -4 to 24 deg at zero deg sideslip angle and for sideslip angles from -12 to 12 deg at angles of attack of 5, 10, 15, and 20 deg. Six-degrees-of-freedom motion simulation studies were used to assess the effect of hysteresis in the rolling-moment coefficient on the prediction of aircraft motion. Simulations of various flight maneuvers were conducted both with and without hysteresis in the aerodynamic data.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE