Investigation on the interference correction of flying wing aircraft rear sting support in high speed wind tunnel test

For the test of a flat-after-body flying wing aircraft model in high speed wind tunnel, the after-body has to be modified to satisfied the attachment of the balance. The deformation and the means of tail support may have some effect on the aerodynamic characteristics of the aircraft, and further affect the cruising efficiency, the trimming angle and the location of the aerodynamic center. On the other hand, there are no commonly used horizontal tail and vertical tail for a flying wing aircraft in order to reduce RCS, the interference of distorted after-body can not to be neglected compares to weak lateral controllability. With the help of CFD and test technique, the distorted after-body support interference has been obtained, in which rear sting is the main support and ventral strut an auxiliary one. The research indicates that the result of the wind tunnel test is accurate and reliable, the correction method can be adopted for the similar configuration model test. The methods of both numerical simulation and wind tunnel tests have been used to correct tail support interference of a flying wing model successfully.