![]() The thrust reversing capabilities of reverser panels installed on the two-dimensional wedge center body were very effective for static or in-flight operation. Significant jet-induced lift was obtained on an aft-mounted lifting surface using a cambered wedge center body to vector thrust. Results indicate that the thrust-minus-aftbody drag performance of the twin two-dimensional nozzle integration is significantly higher, for speeds greater than Mach 0.8, than the performance achieved with twin axisymmetric nozzle installations. An integrated twin-engine/nozzle model, tested with and without empenage surfaces, included cruise, acceleration, thrust vectoring and thrust reversing nozzle operating modes. An isolated single-engine/nozzle model was used to study the effects of internal expansion area ratio, aftbody cowl boattail angle, and wedge length. Two-dimensional wedge nozzle performance characteristics were investigated in a series of wind-tunnel tests. Investigation of two-dimensional wedge exhaust nozzles for advanced aircraft The strongest gradients in stress and shear occur at the base of the plow where the dissipation rate is therefore highest. The stress and velocity fields are calculated from the numerical simulations and show the existence of a shear band under the wedge and that the pressure is nonhydrostatic. We found a universal effective friction law that accounts for the dependence on all the above-mentioned parameters. These constants of proportionality vary with the angle of attack but not (or only weakly) on the velocity. We show that a steady wedge of grains is moved in front of the plow and that the lift and drag forces are proportional to the weight of this wedge. In particular, we investigated the influence of the horizontal velocity of the plate and its angle of attack. We studied the drag and lift forces acting on an inclined plate while it is dragged on the surface of a granular media, both in experiment and in numerical simulation. Percier, Baptiste Manneville, Sebastien McElwaine, Jim N Morris, Stephen W Taberlet, Nicolas Lift and drag forces on an inclined plow moving over a granular surface. These findings give a complete description of all possible processes of dusty shock reflection over a double wedge and may be useful for better understanding the non-equilibrium shock reflection over complex structures. As a result, the shock reflection is far more complicated than the pure gas counterpart and eleven transition processes are found under various wedge angles. For a double wedge with L1 shorter than λ, the non-equilibrium effect manifests more evidently, i.e., three parts of the dusty shock system including the frozen shock, the relaxation zone, and the equilibrium shock together dominate the reflection process. For a double wedge with L1 relatively longer than the particle relaxation length λ, the equilibrium shock dominates the shock reflection and seven typical reflection processes are obtained, which is similar to the pure gas counterpart. Specifically, it behaves differently for double wedges with different length scales of the first wedge L1. The non-equilibrium effect caused by the particle relaxation is found to significantly influence the shock reflection process. The dusty shock reflection over a double wedge with different length scales is systematically studied using an adaptive multi-phase solver. Numerical study on dusty shock reflection over a double wedge ![]() Results obtained from manual calculations and fluent analysis are cross checked. MATLAB is used to form a code for obtaining shock angle with Mach number and wedge angle at the given parameters. Manual calculations for oblique shock properties are calculated with the help of Microsoft excel. Analysis is carried out using fluent at standard conditions with specific heat ratio taken as 1.4. Double wedge airfoil is analysed at different Angles of attack (AOA) based on the wedge angle. Available Computational tools are utilized for analysis. Physical parameters considered for the Double wedge case with wedge angle (ranging from 5 degree to 15 degree. Mach number range taken is for transonic and supersonic. The present work is based on the effects of change in physical parameter for the Double wedge airfoil. ![]() Airfoil shapes differ based on the applications, hence the airfoil shapes considered for supersonic speeds are different from the ones considered for Subsonic. Aerodynamic analysis is part of the whole procedure, which includes focusing on airfoil shapes which will permit sustained flight of aircraft at these speeds. Samanyu, S.Īeronautical studies are being focused more towards supersonic flights and methods to attain a better and safer flight with highest possible performance. Aerodynamic Analysis Over Double Wedge Airfoil
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