Experimental and CFD Contribution to Understanding Delta Wing Vortical Flow

What was learned from the new VFE-2 experiments

“…The measurements were accompanied by numerical investigations to support the interpretation of the flow physics, and in the present paper only limited numerical details are used similarly. The history of VFE-2 has been described by D. Hummel 7 , and the authors [8][9][10][11][12] of the experimental contributions to VFE-2 have presented their work in separate papers. The main results of the new experiments within VFE-2 are summarized below.…”

High-order discontinuous Galerkin RANS solutions of the incompressible flow over a delta wing

“…Fig. 21 reports the computed lift and drag coefficients, achieved with the higher-order polynomial approximation on the coarse grid, and the experimental data at Re = 10 6 of LeRoy et al [41], the resulting correspondence appears quite satisfactory. Looking at this figure it is also clear that our results are quite insensitive to the Reynolds number and even to the use of the transition model.…”

Application of a Semi-Empirical Method to Model Subsonic Vortex Lift over Sharp Leading-Edge Delta Wings

“…The first case is based on the ONERA wind tunnel test campaign which provided experimental results performed in a low subsonic wind tunnel, at a Mach Number of 𝑀 = 0.133 and at a Reynolds Number of 𝑅𝑒 𝑚𝑎𝑐 = 10 6 , for a range of angles of attack of [−8°; 40°] [5]. Aerodynamic forces were expressed as axial and normal force coefficients.…”

“…The results obtained from the semi-empirical method were compared to subsonic experimental data collected for a 65° sweep symmetrical delta wing (case 1) [5]. The experiments were performed in a low subsonic wind tunnel, at a Mach Number of 𝑀 = 0.133 and a Reynolds Number of 𝑅𝑒 𝑚𝑎𝑐 = 10 6 [6].…”