Vladislav Klein Patrick C Murphy Timothy J Curry and Jay M Brandon 1997

Abstract:  this report is to (a) document static and small-amplitude oscillatory data for qualitative assessment; (b) determine a mathematical model with unsteady aerodynamic terms for oscillatory data at different angles of attack and frequencies. The parameters in a model for small-amplitude oscillatory data were estimated by a nonlinear estimation technique of reference?1. Then, a new procedure using splines for model formulation and linear regression was applied. The report begins with a description of the experiment. The results from static and oscillatory test are then described followed by model structure determination and parameter estimation from oscillatory data at various angles of attack and frequencies. The report is completed by concluding remarks. MODEL AND TESTS A three-view sketch of the 0.10-scale F-16XL model is shown in figure?1 together with some basic model dimensions. Static and dynamic tests were conducted in the NASA Langley 12-Foot Low-Speed Wind Tunnel. For both tests, the model was mounted on a dynamic test rig through a six-component strain-gauge balance. The dynamic test rig is a computer controlled, 5 hydraulically-actuat ed system which was sting-mounted on a C-strut support system. The mounting arrangement rotated the model about the reference center of gravity location of 0.558c , over an angle of attack range of -5? to 80?. The maximum capability of the dynamic test rig was 260 deg/sec pitch rate and 2290 deg/sec