Accession Number : ADP005025

Title :   Standard Dynamics Model Experiments with the DFVLR/AVA Transonic Derivative Balance,

Corporate Author : INSTITUT FUER AEROELASTIK GOETTINGEN (GERMANY F R)

Personal Author(s) : Schmidt,E.

Report Date : NOV 1985

Pagination or Media Count : 16

Abstract : A slender high-load forced-oscillation measuring system for dynamic derivatives of aircraft and missile models in a transonic wind tunnel is presented together with typical test results of the significant aerodynamic coefficients and stability derivatives of the Standard Dynamics Model, a simplified fighter aircraft model with a wing span of 0.345 m. The measurements in the rotational modes pitch, yaw and roll encompass Mach numbers from 0.6 to 1.2, angles of attack from 0 to 30 degrees and excitation frequencies from 2 to 20 Hz at a constant Reynolds number of 7.8 Mio/m. Most of the stiffness and damping derivatives gathered show substantial nonlinear dependence on Mach number and angle of attack, where-as the influence of reduced frequency is less prominent. The results are closely related to published measurements on Standard Dynamic models performed in other NATO countries.

Descriptors :   *TRANSONIC CHARACTERISTICS, AERODYNAMIC STABILITY, COEFFICIENTS, GUIDED MISSILE MODELS, AIRCRAFT MODELS, JET FIGHTERS, EXCITATION, DAMPING, STIFFNESS, PITCH(MOTION), ROLL, YAW, MEASURING INSTRUMENTS, DERIVATIVES(MATHEMATICS), REYNOLDS NUMBER, SUBSONIC CHARACTERISTICS, TRANSONIC WIND TUNNELS, WEST GERMANY

Distribution Statement : APPROVED FOR PUBLIC RELEASE