Zobrazeno 1 - 10
of 16
pro vyhledávání: '"Vaitla, Laxman"'
Autor:
Sankarasubramanian, R., Sridhar, Adithya, Prashanth, M.S., Mohammad, Akram, Velamati, Ratna Kishore, Vaitla, Laxman
Publikováno v:
In Aerospace Science and Technology October 2018 81:333-347
Publikováno v:
Journal of Wind Engineering and Industrial Aerodynamics. 158:98-108
In practical situations, it is important to analyze the performance of VAWT considering the fluctuations of free stream wind. In the present paper, 3D unsteady numerical analysis is employed to investigate the effect of fluctuating wind conditions on
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0f9d2978e93408f58aa84ff734678e1f
https://doi.org/10.1016/j.jweia.2016.10.001
https://doi.org/10.1016/j.jweia.2016.10.001
Akademický článek
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Publikováno v:
Aircraft Engineering and Aerospace Technology. 86:375-384
Purpose – The purpose of the present paper is to obtain the capability of designing modern rotorcrafts with enhanced accuracy and reliability. Design/methodology/approach – Among the existing rotorcraft design programs, an appropriate program was
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::40710b41e812c7902de2b368773d2c79
https://doi.org/10.1108/aeat-10-2012-0177
https://doi.org/10.1108/aeat-10-2012-0177
Publikováno v:
Journal of Aerospace Engineering. 26:555-570
Rotary wing aeroelasticity is a highly complex phenomenon involving coupling between flexible blade dynamics and unsteady aerodynamics including stall and unsteady wake effects. In this paper, a low-cost computational aeroelastic model including the
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5b91b89767374700262060251bfc83b7
https://doi.org/10.1061/(asce)as.1943-5525.0000168
https://doi.org/10.1061/(asce)as.1943-5525.0000168
Publikováno v:
Journal of Aerospace Engineering. 24:378-388
Compared with those of a fixed-wing aircraft, the dynamics of a rotorcraft are significantly more complex. One of the major challenges in the design of an autonomous helicopter is the development of a flight dynamic model, which can be useful for sim
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::60d9fb96bd9a1e74b3467dbdb97f769c
https://doi.org/10.1061/(asce)as.1943-5525.0000065
https://doi.org/10.1061/(asce)as.1943-5525.0000065
Publikováno v:
International Journal of Aeronautical and Space Sciences. 12:156-162
The preliminary design stage of helicopters consists of various operations and in each operation design several detailed analysis tasks are needed. The analysis tasks include performance and the required power estimation. In helicopter design, those
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d24897a37687724f37bc75323d6400c0
https://doi.org/10.5139/ijass.2011.12.2.156
https://doi.org/10.5139/ijass.2011.12.2.156
Autor:
Comandur Venkatesan, Vaitla Laxman
Publikováno v:
Journal of the American Helicopter Society. 54:32001-3200118
Flight test data of helicopters indicate that vibratory levels in the fuselage exhibit a wide spectrum of frequencies including the dominant blade passage frequency and its integer multiples. The present work attempts to understand the reason for the
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::fe1f06ce21d6941df15a1f41c0bdb1b9
https://doi.org/10.4050/jahs.54.032001
https://doi.org/10.4050/jahs.54.032001
Autor:
Vaitla Laxman, Comandur Venkatesan
Publikováno v:
AIAA Journal. 45:271-280
Flight-test data of helicopters indicate that vibratory levels in the fuselage exhibit a wide spectrum of frequencies, including a few below the rotor revolutions per minute. It is well known that helicopter blades operate in a complex aerodynamic en
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a50a42eab5dcde23456e4bd5cd5ba4f8
https://doi.org/10.2514/1.24587
https://doi.org/10.2514/1.24587
Publikováno v:
52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference.
An initial version of an advanced rotorcraft preliminary design optimization framework was developed previously. For its further improvement, a new trim and performance subroutines based on the blade element theory is developed and incorporated. Such
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4d5e89474fd14ba64c58ef56ad2e80e3
https://doi.org/10.2514/6.2011-1831
https://doi.org/10.2514/6.2011-1831