Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight

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BENGIN, Aleksandar ;MITROVIĆ, Časlav ;BEKRIĆ, Dragoljub ;PEŠIĆ, Slavko ;CVETKOVIĆ, Dragan .
Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. 
Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 54, n.3, p. 170-178, august 2017. 
ISSN 0039-2480.
Available at: <https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/>. Date accessed: 30 may. 2020. 
doi:http://dx.doi.org/.
Bengin, A., Mitrović, ., Bekrić, D., Pešić, S., & Cvetković, D.
(2008).
Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight.
Strojniški vestnik - Journal of Mechanical Engineering, 54(3), 170-178.
doi:http://dx.doi.org/
@article{.,
	author = {Aleksandar  Bengin and Časlav  Mitrović and Dragoljub  Bekrić and Slavko  Pešić and Dragan  Cvetković},
	title = {Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {54},
	number = {3},
	year = {2008},
	keywords = {unsteady aerodynamics; helicopter rotor blade; potential flow; lifting surface theory; },
	abstract = {This paper presents the numerical model developed for rotor blade aerodynamicsloads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent bothtrailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independentof time, and it depends on circulation gradient at the point of vortex element released from the blade.},
	issn = {0039-2480},	pages = {170-178},	doi = {},
	url = {https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/}
}
Bengin, A.,Mitrović, .,Bekrić, D.,Pešić, S.,Cvetković, D.
2008 August 54. Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 54:3
%A Bengin, Aleksandar 
%A Mitrović, Časlav 
%A Bekrić, Dragoljub 
%A Pešić, Slavko 
%A Cvetković, Dragan 
%D 2008
%T Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
%B 2008
%9 unsteady aerodynamics; helicopter rotor blade; potential flow; lifting surface theory; 
%! Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
%K unsteady aerodynamics; helicopter rotor blade; potential flow; lifting surface theory; 
%X This paper presents the numerical model developed for rotor blade aerodynamicsloads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent bothtrailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independentof time, and it depends on circulation gradient at the point of vortex element released from the blade.
%U https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/
%0 Journal Article
%R 
%& 170
%P 9
%J Strojniški vestnik - Journal of Mechanical Engineering
%V 54
%N 3
%@ 0039-2480
%8 2017-08-21
%7 2017-08-21
Bengin, Aleksandar, Časlav  Mitrović, Dragoljub  Bekrić, Slavko  Pešić, & Dragan  Cvetković.
"Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight." Strojniški vestnik - Journal of Mechanical Engineering [Online], 54.3 (2008): 170-178. Web.  30 May. 2020
TY  - JOUR
AU  - Bengin, Aleksandar 
AU  - Mitrović, Časlav 
AU  - Bekrić, Dragoljub 
AU  - Pešić, Slavko 
AU  - Cvetković, Dragan 
PY  - 2008
TI  - Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
JF  - Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - unsteady aerodynamics; helicopter rotor blade; potential flow; lifting surface theory; 
N2  - This paper presents the numerical model developed for rotor blade aerodynamicsloads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent bothtrailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independentof time, and it depends on circulation gradient at the point of vortex element released from the blade.
UR  - https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/
@article{{}{.},
	author = {Bengin, A., Mitrović, ., Bekrić, D., Pešić, S., Cvetković, D.},
	title = {Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {54},
	number = {3},
	year = {2008},
	doi = {},
	url = {https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/}
}
TY  - JOUR
AU  - Bengin, Aleksandar 
AU  - Mitrović, Časlav 
AU  - Bekrić, Dragoljub 
AU  - Pešić, Slavko 
AU  - Cvetković, Dragan 
PY  - 2017/08/21
TI  - Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight
JF  - Strojniški vestnik - Journal of Mechanical Engineering; Vol 54, No 3 (2008): Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - unsteady aerodynamics, helicopter rotor blade, potential flow, lifting surface theory, 
N2  - This paper presents the numerical model developed for rotor blade aerodynamicsloads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent bothtrailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independentof time, and it depends on circulation gradient at the point of vortex element released from the blade.
UR  - https://www.sv-jme.eu/article/improved-solution-approach-for-aerodynamics-loads-of-helicopter-rotor-blade-in-forward-flight/
Bengin, Aleksandar, Mitrović, Časlav, Bekrić, Dragoljub, Pešić, Slavko, AND Cvetković, Dragan.
"Improved solution approach for aerodynamics loads of helicopter rotor blade in forward flight" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 54 Number 3 (21 August 2017)

Authors

Affiliations

  • University of Belgrade, Faculty of Mechanical Engineering, Serbia
  • University of Belgrade, Faculty of Mechanical Engineering, Serbia
  • University of Belgrade, Faculty of Mechanical Engineering, Serbia
  • University of Belgrade, Faculty of Mechanical Engineering, Serbia
  • University of 'Singidunum' Belgrade, Faculty of Business Information Science, Serbia

Paper's information

Strojniški vestnik - Journal of Mechanical Engineering 54(2008)3, 170-178

This paper presents the numerical model developed for rotor blade aerodynamicsloads calculation. The model is unsteady and fully three-dimensional. Helicopter blade is assumed to be rigid, and its motion during rotation is modeled in the manner that rotor presents a model of rotor of helicopter Aerospatiale SA 341 "Gazelle" (the blade is attached to the hub by flap, pitch and pseudo lead-lag hinges). Flow field around the blade is observed in succession of several azimuth locations. Flow field around helicopter rotor is modeled as fully three-dimensional, unsteady and potential. Blade aerodynamics is modeled using a lifting surface model. Rotor wake is generated from the straight elements of constant vorticity, released from the trailing edge, at fixed azimuth angles. These vortices represent bothtrailed and shed wake components, and are allowed to freely convect along local velocity vectors. Wake is modeled as free one, and its shape at certain moment can be calculated from simple kinematics laws applied on collocation points of the wake. Wake distortion is calculated only in the rotor near-field, i.e. in finite number of rotor revolutions. Vortex elements are modeled with vortex core. The radius of the vortex core is assumed independentof time, and it depends on circulation gradient at the point of vortex element released from the blade.

unsteady aerodynamics; helicopter rotor blade; potential flow; lifting surface theory;