An Efficient and Robust Method for Predicting Helicopter Rotor High-speed Impulsive Noise

A new formulation for the Ffowcs Williams{ Hawkings quadrupole source, which is valid for a fareld in-plane observer, is presented. The fareld approximation is new and unique in that no further approximation of the quadrupole source strength is made and integrands with r 2 and r 3 dependence are retained. This paper focuses on the development of a retarded-time formulation in which time derivatives are analytically taken inside the integrals to avoid unnecessary computational work when the observer moves with the rotor. The new quadrupole formulation is similar to Farassat's thickness and loading formulation 1A. Quadrupole noise prediction is carried out in two parts: a preprocessing stage in which the previously computed ow eld is integrated in the direction normal to the rotor disk, and a noise computation stage in which quadrupole surface integrals are evaluated for a particular observer position. Preliminary predictions for hover and forward ight agree well with experimental data. The method is robust and requires computer resources comparable to thickness and loading noise prediction.