Eunju KIM, Soo Hyung PARK
DOI Number: XXX-YYY-ZZZ
Conference number: HiSST 2024-0050
It is essential to measure its aerodynamic coefficients to evaluate the aerodynamic characteristics of an aircraft. Various methodologies have been developed for this specific purpose. Among these methodologies, the approach utilizing a balance is the most prevalent. In this approach, the model is mounted on a sting, which has raised a significant issue due to the presence of the sting, leading to the generation of additional drag [1]. Obtaining dynamic stability derivatives requires additional experiments such as the forced vibration method. In order for the model to fly at 6-DOF (Degrees of Freedom), the sting must be removed. This technique is known as free-flight technique, allowing experiments in a dynamic environment closely resembling actual flight conditions. The coefficients obtained through the free-flight method are combine static and dynamic coefficients. Therefore, by separating these aerodynamic coefficients into static and dynamic coefficients, it becomes possible to acquire both types of coefficients in a single experiment. This method appears to be more efficient compared to the balance method, which requires additional experiments to obtain dynamic stability. In this study, a damping free-flight model was designed to obtain both static and dynamic coefficients. A free-flight experiment was conducted in KULT (Konkuk University Ludwieg Tube) [2]. The AOA (Angle of Attack) for the model was determined from the images using a technique called the Hough Algorithm. The AOA of the model can be obtained through the slope of the straight line. In addition, x,y velocity can be obtained through both end points. The aerodynamic coefficients obtained through the free-flight experiment are the sum of the static and dynamic coefficients. In this study, Scikit-Learn technique was used to separate the coefficients into static and dynamic derivatives.