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http://dx.doi.org/10.5139/JKSAS.2021.49.2.85

Study on the Correction of a Wing-tail Interference Effect in a Semi-empirical Aerodynamic Analysis Tool  

Lee, Dae-Yeon (System Design & Performance Analysis Group, LIG Nex1)
Kim, Jae-Hyun (System Design & Performance Analysis Group, LIG Nex1)
Kang, Dong-Gi (System Design & Performance Analysis Group, LIG Nex1)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.49, no.2, 2021 , pp. 85-93 More about this Journal
Abstract
In this paper, the aerodynamic characteristics of general tail controlled missile were predicted and corrected the result using semi-empirical analysis tool. The cause of the error was confirmed by comparing the aerodynamic characteristics prediction result of the semi-empirical analysis tool with the wind tunnel test result, and the main error factor of the semi-empirical analysis tool was the interference component between the main wing and the tail wing. The semi-empirical analysis results were corrected using the wind tunnel test results and the computational analysis results, and it was confirmed that the corrected data agrees well with the wind tunnel test results. Through this study, it was confirmed that the wing-tail interference component correction is needed when predicting the aerodynamic characteristics of a general tail controlled missile using a semi-empirical analysis tool.
Keywords
Tail-Controlled Missile; Wing-Tail Interference; Semi-Empirical Analysis Tool;
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  • Reference
1 Chin, S. S., Missile Configuration Design, McGraw-Hill, 1961.
2 Monta, W. J., "Supersonic Aerodynamic Characteristics of a Sparrow III Type Missile Model with Wing Controls and Comparison with Existing Tail-Control Results," NASA TP 1087, 1977.
3 Cho, T. H., Kim, M. D. and Hyun, J. S., "Wind Tunnel Investigation of the Effect of Lifting Surface Shapes on a Wing-Body-Tail Missile at Supersonic Speed," International Conference on Method and Means for Experimental Investigation in Aerodynamics, Russia, 1993.
4 Han, M. S., Myong, R. S., Cho, T. H., Hwang, J. S. and Park, C. H., "Analysis of the Aerodynamic Characteristics of Missile Configurations Using a Semi-Empirical Method," Journal of the Korean Society for Aeronautical and Space Sciences, 2005.3, pp. 26-31
5 Blake, W. B., "MISSILE DATCOM User's manual-1997 Fortran 90 Revision," Air Force Research Laboratory, February 1998.
6 Yoon, S. J., "Some Trends in Aerodynamic Analysis Methods," Journal of the Korean Society for Aeronautical and Space Sciences, 1994, pp. 107-116.
7 Thomas, J. S. and Rebecca, Z. S., "Aerodynamic Predictions, Comparisons, and Validations Using Missile DATCOM(97) and Aeroprediction 98 (AP98)," Journal of Spacecraft and Rockets, Vol. 42, No. 2, 2005, pp. 257-265   DOI
8 Kim, D. H., Lee, D. Y., Kang, D. G. and Lee, H. J., "A wing-tail interference for a tail-controlled missile," Journal of the Korean Society for Aeronautical and Space Sciences, 2017, pp. 817-824.
9 Moore, F. G. and Moore, L. Y., "2009 Version of the Aeroprediction Code: AP09," Journal of Spacecraft and Rockets, Vol. 45, No. 4, 2008, pp. 677-690   DOI
10 Moore, F. G. and Moore, L. Y., "Approximate Method to Calculate Nonlinear Rolling Moment due to Differential Fin Deflection," Journal of Spacecraft and Rockets, Vol. 49, No. 2, 2012, pp. 250-260.   DOI
11 Graves, E. B. and Fournier, R. H., "Stability and Control Characteristics at Mach Numbers from 0.20 to 4.63 of a Cruciform Air-to-Air Missile with Triangular Canard Controls and a Trapezoidal Wing," NASA TM X-3070, 1974.
12 Blair, A. B., Allen, J. M. and Hernandez, G., "Effect of Tail-Fin Span on Stability and Control Characteristics of a Canard-Controlled Missile at Supersonic Mach Numbers," NASA TP 2157, 1893.
13 Hemsch, M. J., "The Component Build-Up Method for Engineering Analysis of Missiles at Low-to-High Angles of Attack," Tactical Missile Aerodynamics: Prediction Methodology, AIAA, 1992.