Evaluation of wind tunnel test data from a helicopter model with novel fuselage geometry and additional passive lift devices

Abstract

In the framework of the DLR guiding concept 4 "The Rescue Helicopter 2030" a new medium size wind tunnel model was developed. Two wind tunnel test campaigns were conducted where a number of new ideas were tested like a lower drag optimized fuselage and the option of side wings. The basic model setup without rotor blades was tested first in 2020, where the aerodynamic properties of two different fuselages were measured. In 2024 the model was completed with a spinning rotor and further instrumentation. A sophisticated Data Acquisition System was developed for measuring data from the rotating domain. A completely new set of rotor blades with instrumentation was manufactured inhouse. Two wings were designed and manufactured, which could be mounted optionally at the main model structure. This paper evaluates the measured data from sensors in the rotating and non-rotating frame.