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Batina’s work and uses an F-16 half-span model with the Computational Aeroelasticity Program
Transonic Small-Disturbance (CAP-TSD). He examines steady flow solutions and compares
these to wind-tunnel test results. 62 Pitt 63 applies the CAP-TSD approach to transonic flutter
analysis of the F-15 and F/A-18.
Denegri 64,65 applies the medium-fidelity time-domain computational physics approach of
CAP-TSD to LCO prediction and extends the steady CAP-TSD analysis of Batina and Haller and
the transonic flutter analysis of Pitt by examining a typical F-16 LCO test case. 23,24
Discrepancies between the aerodynamic model and the wind tunnel and CFD results are noted
and may be the primary causes of the observed differences between the aeroelastic
computational and flight test results. Denegri continues to apply the CAP-TSD approach in the
Medium-Fidelity Flutter Analysis Tool (MEDFFAT). 66 MEDFFAT overcomes the linear
transonic physics limitations of current commercial off-the-shelf (COTS) software by
automatically generating transonic computational grids for the aircraft and its stores based on a
single linear panel model, solving the nonlinear aeroelastic equations, and interpolating the
solutions between the aircraft and stores grids.
NONLINAE
Cunningham develops NONLINAE, a semi-empirical method for LCO prediction based on
his observation of shock induced trailing edge separation (SITES) during LCO wind tunnel
testing. 67-72 He shows that nonlinear aerodynamic forces arising from SITES are a dominant
mechanism in transonic LCO. He investigates several transonic LCO cases and demonstrates
success with an analytical approach, NONLINAE, which uses both steady and unsteady wind-
tunnel data for the aerodynamic forces and a linear dynamics model for the structural motions.
His time lag-based model shows good correlation to test results for configurations that exhibit
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