This paper is based on Slovak Space Tech Day 2 & Slovak Aviation Industry Day keynote speech from Hironobu Kondo and Martin Hegedűš. It shortly described All Nippon Airways (ANA) as a company and the trends and issues of the aviation industry from ANA perspective, furthermore future projects and prospects. It gave insights into the efforts of ANA to battle the carbon footprint of the company, social aspects of the globalized world, and cooperation of multiple elements to achieve a better and more sustainable future for all of us, nonetheless measures taken to fight against the spreading of the Covid-19. Information was obtained from official All Nippon Airways sources, statistics, and press releases. To conclude paper described the reason and significance of aviation and the need to adjust according to the new standards.

This paper presents summarized descriptions and applications of engineering, intermediate, and high level missile aerodynamics prediction methods developed and/or used by NEAR. The engineering level method is represented by the M3HAX experimental data based code, the intermediate level method includes the analytical panel-method based SUPDL/SUBDL and modified linear theory VTXCHN codes, and the high level methods include the NEARZEUS space marching Euler flow solver. All of the methods contain models to account for fin and body vorticity effects in the aerodynamic loads. The engineering and intermediate level methods are applied to the prediction of high angle of attack pitch plane and lateral aerodynamic characteristics of missiles at arbitrary roll angle and aerodynamic loads acting on conventional and chined body shapes, and to assess effects of fin-body gap on fin loads. The intermediate level methods are also employed in the design of nonconventional fin planforms for minimum hinge moment The Euler flow solver is applied to the prediction of rolling moments acting on a canard configuration. Comparisons with experimental data are presented It is concluded that the missile aerodynamicist and/or designer should be aware of the availability and utility of the various levels of missile aerodynamics prediction methodology.

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Descriptions and applications of engineering-, intermediate-, and high-level missile aerodynamics prediction methods are presented. The engineering-level method is represented by an experimental data-based code, the intermediate-level method includes enhanced panel method-based codes and a modi ed linear theory code, and the high-level methods include a space-marching Euler ow solver. All of the methods contain n and body vorticity models. The engineering-and intermediate-level methods are applied to the prediction of high-angle-of-attackpitch plane and lateral aerodynamic characteristics of missiles at arbitrary roll angle, to aerodynamic loads acting on conventional and chined body shapes, and to assess effects of n-body gap on n loads. The intermediate-level methods are also employed in the design of nonconventional n planforms for minimum hinge moment. The Euler ow solver is applied to the prediction of rolling moments acting on a canard con guration. Comparisons with experimental data are presented. The conclusion is made that the missile aerodynamicist and/or designer should be aware of the availability and should make use of the various levels of missile aerodynamics prediction methodology. NomenclatureC A; C A = axial force coef cient, positive aft along x direction; axial force/q 1 S REF C BM = lifting-surface bending moment coef cient, positive side edge up; bending moment/q 1 S FIN L REF Marnix F. E. Dillenius received his B.S. (with honors), M.S., and Ph.D. degrees in mechanical engineering from the University of California, Berkeley, in 1962, 1964, and 1968, respectively. In 1969, he joined Nielsen Engineering and Research (NEAR), where he was involved in modeling aerodynamic interference, standard takeoff and landing aerodynamics, and trailing-wake vortex studies. He originated and/or made major contributions to analytical investigations concerning supersonic wing loading theories, external store separation characteristics, and detailed missile aerodynamic prediction methods. Dr. Dillenius has been president of NEAR since 1992. He is an Associate Fellow of the AIAA. Daniel J. Lesieutre received his B.S. and M.S. degrees in aeronautical and astronautical engineering from Purdue University in 1983 and 1985, respectively. Since joining NEAR, he has directed research in applied aerodynamics, aerodynamic shape optimization, aeroelastic n design, and unsteady aerodynamics. He has participated in projects involving hydrodynamics, missile, aircraft and launch vehicle aerodynamics, and store separation. He has successfully demonstrated the use of numerical optimization methods for the multidisciplinary design of control ns with geometric and structural constraints. He is a Senior Member of the AIAA. Martin C. Hegedus received his B.S. degree in 1990 from the University of California, Davis, and an M.S. in aeronautics and astronautics from Stanford University in 1992. Since joining NEAR in 1994, he has worked on the development of aerodynamic and store separation prediction codes and graphical user interfaces...

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