Testing of ONERA Model
Sagar P R1, N.Muthuswamy2, C. Senthil Kumar3
1Sagar P R,  Assistant Professor, Department of Aerospace Engineering, PVP Siddhartha Institute of Technology, Vijayawada (A.P.), India.
2N.Muthuswamy, Professor, REC, Chennai, India.
3Dr. C. Senthil Kumar,  Associate Professor, Department of Aerospace Engineering, Madras Institute of Technology, Anna University, Chennai, India.
Manuscript received on November 07, 2014. | Revised Manuscript received on November 21, 2014. | Manuscript published on December 30, 2014. | PP: 34-36  | Volume-4 Issue-2, December 2014. | Retrieval Number:  B3589124214/2013©BEIESP

Open Access | Ethics and Policies | Cite
© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)

Abstract: The aim of the project is to estimate of the aerodynamic coefficients of the ONERA M4 using section positioning mounting mechanism, six component balance and integrated data acquisition system. A wing-body-tail with and without winglets model of ONERA M4 model of suitable scale to fit in the test section of our subsonic wind tunnel is designed and fabricated with pressure ports at suitable points. The model is to be tested at various pitch angles from -10° to 30°, in steps of 10 degrees and yaw angle is varied from -30 degree to +30 degree in steps of 10 degrees. For each pitch and yaw angle the rpm is varied from 300 to 600 in steps of 60 and the variation of coefficient of pressure on the surface of the model is determined using a suitable data acquisition system. The experiment is done for all yaw angle and readings are taken for the model. The aerodynamic coefficients are calculated for the model. Aerodynamic coefficient plots are made for different rpm and pitch angle. Comparison charts are made by keeping rpm as constant in one case and pitch angle as constant in the other. Variations are observed and are validated using theoretical results. Similar experimental procedure should be followed for all the yaw angles in case model with winglets and finally a comparative study is made on the experimental studies. The experimental observations should be compared with computational results for validation.
Keywords: Aerodynamic testing, Subsonic flow, Wind tunnel, Force measurements, ONERA M4 model.