Numerical prediction and wind tunnel experiment for a pitching unmanned combat air vehicle

Abstract

The low-speed flowfield for a generic unmanned combat air vehicle (UCAV) is investigated both experimentally and numerically. A wind tunnel experiment was conducted with the Boeing 1301 UCAV at a variety of angles of attack up to 70 degrees, both statically and with various frequencies of pitch oscillation (0.5, 1.0, and 2.0 Hz). In addition, pitching was performed about three longitudinal locations on the configuration (the nose, 35% MAC, and the tail). Solutions to the unsteady, laminar, compressible Navier-Stokes equations were obtained on an unstructured mesh to match results from the static and dynamic experiments. The computational results are compared with experimental results for both static and pitching cases. Details about the flowfield, including vortex formation and interaction, are shown and discussed, including the non-linear aerodynamic characteristics of the vehicle. Published by Elsevier Masson SAS.

Evaluation of DES for weapons bays in UCAVs

“…This is not always the case though. Experiments by Forestier et al [11] on a cavity with an L/D ratio of 0.42 found that the shear had an high growth rate for the first 25% of the length (dδ m /dx = 0.12), which then reduced to a lower value (dδ m /dx = 0.042). This was also observed numerically by Larchevêque et al [23] for the same cavity.…”

“…Cummings et al [10] experimentally and numerically investigated a similar configuration designated 1301. Similar to the studies of the 1303 UCAV, agreement between the experimental and numerical data sets was only gained at angles of attack below 15 degrees.…”

Experimental research into aerodynamic characteristics of the model of a maneuvered aircraft with an airflow passage through engines

“…Experimental and numerical research into a low-velocity flow field for an unmanned AC were undertaken [20]. Experiment during WTT was conducted statically with different angles of attack up to 70°.…”

Flow over 50o Delta Wings with Different Leading-Edge Radii

“…Cummings et al 24 compute the flowfield over a Λ = 50 o UCAV configuration with rounded leading edges at a Re of the order of 10 5 . There is a correspondence between the computed upstream movement of the bursting point with α over the UCAV configuration and the upstream movement of the S 2 bending point observed over wing III.…”