Numerical Study on Variation in Drag Difference by Adding Annular Plug into Flow-Through Nacelle with Integrated Configuration
Author:
Affiliation:
1. Aviation Technology Directorate, Japan Aerospace Exploration Agency
2. Ryoyu Systems Co. Ltd.
3. Sincere Co. Ltd.
4. Adecco Co. Ltd.
Publisher
Japan Society for Aeronautical and Space Sciences
Link
https://www.jstage.jst.go.jp/article/tastj/22/0/22_22.7/_pdf
Reference12 articles.
1. 1) Kimzey, W. F., Covert, E. E., Rooney, E. C., Richey, G. K., and James, C. R.: Thrust and Drag: Its Prediction and Verification, American Institute of Aeronautics and Astronautics, Reston, 1985.
2. 2) Webb, L. D., Whitmore, S. A., and Janssen, R. L.: Preliminary Flight and Wind Tunnel Comparisons of the Inlet/Airframe Interactions of the F-15 Airplane, AIAA Paper 79-0012, 1979.
3. 3) Yamada, K., Uchiyama, T., and Ueno, M.: Capture Area Ratio and Drag Difference between Wind Tunnel and Flight Tests, Trans. Jpn. Soc. Aeronaut. Space Sci., 65, 3 (2022), pp. 134–137.
4. 4) Re, R. J.: An Investigation of Several NACA 1-Series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29, NASA TM X-2917, 1974.
5. 5) Goulos, I., Otter, J., Tejero, F., Rebessa, J. H., MacManus, D., and Sheaf, C.: Civil Turbofan Propulsion Aerodynamics: Thrust-drag Accounting and Impact of Engine Installation Position, Aero. Sci. Techol., 111 (2021), 106533.
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