Revised Results of the Unsteady Transonic Pressure Measurements on the Lann Model.

摘要

A new postprocessing procedure is applied on the data, acquired in 1981 during the unsteady transonic pressure measurements on a transport-type supercritical wing (LANN-model), oscillating in pitch. The new procedure takes into account the influence of the local boundary layer on the dynamic response of the pressure tubes. The report presents aerodynamic coefficients of which the accuracy has been improved by application of this new procedure.