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New facility for experimental and computational studies of sonic boom from aircraft is designed and manufactured in TsAGI. The equipment was mounted in supersonic wind tunnel with 0.6×0.6 m cross section. Tests were performed at Mach numbers 1.75, 2.0 and 2.25 with the use of two different models, the first being the cone-cylinder body and the second is the simplified supersonic airplane configuration with the triangle wing. The method implies the application of fluorescent pressure-sensitive paints for measurements of pressure distribution in the near field of the model. The experimental facility was designed using modern CFD approaches. Pressure distributions obtained in the near field of the model using the experimental method are compared with numerical simulations based on the software package ANSYS CFX. This comparison enables to estimate the possibilities of both the experiment and numerical simulation in prediction of the shock waves formation in the near-field of the disturbed flow.

DEVELOPMENT OF PHYSICAL METHODS OF THE SUPERSONIC AIRPLANE NEAR-FIELD INVESTIGATION AIMED AT THE SONIC BOOM MINIMIZATION