Prediction of Aerodynamic Stability Derivatives of Shell Configuration of Missile Using CFD Method

Kang, Eunji

doi:2020.23.4.363

J. KIMS Technol > Volume 23(4); 2020 > Article

Research Paper

열·유체 부문

Journal of the Korea Institute of Military Science and Technology 2020;23(4):363-370.
DOI: https://doi.org/10.9766/KIMST.2020.23.4.363 Published online August 5, 2020.

Prediction of Aerodynamic Stability Derivatives of Shell Configuration of Missile Using CFD Method

Eunji Kang

The 1st Research and Development Institute, Agency for Defense Development, Korea

CFD를 이용한 유도탄 덮개 형상의 공력 미계수 예측

강은지

국방과학연구소 제1기술연구본부

Correspondence: Eunji Kang,
Email: aerokang@add.re.kr

Received: 5 June 2020; Revised: 8 July 2020; Accepted: 10 July 2020;

Abstract

In this study, pitching stability derivatives of the conical shell configuration is predicted using commercial CFD code. Unsteady flow analysis with forced harmonic motion of the model is performed using overset mesh. The test is conducted about Basic finner missile configuration. The static and dynamic stability derivatives are good agreement with available experimental data. As the same way, a conical shell is analyzed in Mach number 1.6 and various reduced frequency. The static and dynamic derivatives are obtained from the time-pitching moment coefficient histories in each of four cases of mean angle of attack. The variation of reduced frequency is not affected static and dynamic derivatives. Increasing the mean angle of attack, static derivatives are increased slowly. Comparison of the Cm curves at the steady and unsteady state results shows that the Cm curve including the damping effect is lower than otherwise case, approximately 9-18 %.

Key Words: CFD, Stability Derivatives, Conical Shell, Forced Motion, Overset Mesh