Wave-drag characteristics of an over-the-wing nacelle business-jet configuration

This paper presents the wave-drag characteristics of an over-the-wing nacelle configuration. The flow over the wing is accelerated such that the aerodynamic interference between the nacelle and the wing is critical in the transonic flight regime. In general, locating nacelles over the wing causes an, unfavorable aerodynamic interference and induces a strong shock wave, which results in a lower drag-divergence Mach number. If the nacelle is located at the optimum position relative to the wing, however, the shock wave can be minimized, and drag divergence occurs at a Mach number higher than that for the clean-wing configuration. Theoretical analyses and experimental measurements demonstrate that a wave-drag reduction can be achieved by locating the nacelle front face near the shock-wave position on the wing.