For the case of a realistic small-scale “double-stream nozzle–high-lift wing” configuration, a previously developed simplified semiempirical method for calculating the low-frequency noise of jet–wing interaction is tested. As input data for calculating the noise, we used the results of measuring the amplitude and convective velocity of perturbations in the near field of a turbulent jet near the trailing edge of an extended flap. The measurements were performed with a pair of pressure sensors flush-mounted on the lower surface of the wing model. It is demonstrated that the results of the calculated estimate for the spectral characteristics and directivity of the interaction noise agree well with direct noise measurements in the far field both under static conditions and in the presence of coflow simulating the effect of flight.