Luigi Iuspa
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Luigi Iuspa has a total of 14 co-authors. Here are the top co-authors by number of shared publications:
- Antonio Viviani
Dipartimento di Ingegneria, Università degli Studi della Campania, Aversa, Italy
12 shared publications - Andrea Aprovitola
Engineering Department, Università della Campania “L.Vanvitelli”, Via Roma 29, I-81031 Aversa, Italy
11 shared publications - Giuseppe Pezzella
Engineering Department, Università della Campania “L.Vanvitelli”, Via Roma 29, I-81031 Aversa, CE, Italy
9 shared publications Antonio Viviani
2 shared publicationsAndrea Aprovitola
Università della Campania “Luigi Vanvitelli”, Dipartimento di Ingegneria, Via Roma 29, I-81031 Aversa (CE), Italy
1 shared publication- Cinzia Rainone
Università della Campania “Luigi Vanvitelli
1 shared publication
Latest Publications
- 2 June 2025
- Published by Elsevier in Acta Astronautica
- Vol. 235, 339-354
Optimization procedure for wings flying in the Martian atmosphere
- 2 June 2025
- Published by Elsevier in Acta Astronautica
- Vol. 235, 339-354
Optimization procedure for wings flying in the Martian atmosphere
- 16 December 2024
- Published by Elsevier in Aerospace Science and Technology
- Vol. 158
Aeroshape design and low speed aerodynamic analysis of a crew return vehicle
- 16 December 2024
- Published by Elsevier in Aerospace Science and Technology
- Vol. 158
Aeroshape design and low speed aerodynamic analysis of a crew return vehicle
- 16 May 2024
- Published by Elsevier in Acta Astronautica
- Vol. 221, 94-107
Flows past airfoils for the low-Reynolds number conditions of flying in Martian atmosphere
- 16 May 2024
- Published by Elsevier in Acta Astronautica
- Vol. 221, 94-107
Flows past airfoils for the low-Reynolds number conditions of flying in Martian atmosphere
- 23 August 2023
- Published by Elsevier in Acta Astronautica
- Vol. 212, 580-594
Aerodynamic optimization of airfoils shape for atmospheric flight on Mars planet
- 23 August 2023
- Published by Elsevier in Acta Astronautica
- Vol. 212, 580-594
Aerodynamic optimization of airfoils shape for atmospheric flight on Mars planet
- Open Access
A Numerical Procedure for Variable-Pitch Law Formulation of Vertical-Axis Wind Turbines
A numerical procedure was developed to determine a variable-pitch law that maximized the performance of a vertical-axis wind turbine (VAWT). The methodology was based on the determination, for each blade, of the angle of attack maximizing the stationary aerodynamic efficiency at prescribed azimuthal positions. The angles of attack were determined by means of a panel method with a low computational effort, and the methodology was implemented in Matlab software (version R2021a) allowing us to achieve in real time a variable-pitch law suitable for the turbine geometry. The variable pitch law was validated by considering its effect on the torque of a 2D model of an H-Darrieus turbine. U-RANS analyses were carried out with a model and a sliding-mesh technique was used to prescribe the blade motion around the shaft and pitch motion. Results showed how the variable-pitch law delayed the dynamic stall and improved the aerodynamic performance considerably.Open AccessA Numerical Procedure for Variable-Pitch Law Formulation of Vertical-Axis Wind Turbines
A numerical procedure was developed to determine a variable-pitch law that maximized the performance of a vertical-axis wind turbine (VAWT). The methodology was based on the determination, for each blade, of the angle of attack maximizing the stationary aerodynamic efficiency at prescribed azimuthal positions. The angles of attack were determined by means of a panel method with a low computational effort, and the methodology was implemented in Matlab software (version R2021a) allowing us to achieve in real time a variable-pitch law suitable for the turbine geometry. The variable pitch law was validated by considering its effect on the torque of a 2D model of an H-Darrieus turbine. U-RANS analyses were carried out with a model and a sliding-mesh technique was used to prescribe the blade motion around the shaft and pitch motion. Results showed how the variable-pitch law delayed the dynamic stall and improved the aerodynamic performance considerably. - 11 November 2022
- Published by Elsevier in Aerospace Science and Technology
- Vol. 131
Multi-disciplinary optimization of a space re-entry vehicle using skeleton-based integral soft objects
- 11 November 2022
- Published by Elsevier in Aerospace Science and Technology
- Vol. 131
Multi-disciplinary optimization of a space re-entry vehicle using skeleton-based integral soft objects
- Open Access
- 4 May 2022
- Published by IntechOpen
Lifting Entry Analysis for Manned Mars Exploration Missions
In the present work, a feasibility study of a manned Mars entry, descent, and landing mission, performed with a lifting vehicle, is analyzed. Mars entry challenges relate to different atmosphere models; consequently, the effective landing capability of a winged configuration is discussed. An entry trajectory study in the Martian atmosphere assuming both a planar and non-planar three degree-of-freedom model is performed. Peak heat rates and time-integrated heat loads during the descent are computed verifying the entry corridor. It is shown that prescribed aerodynamic performances can be modulated explicitly by varying angle of attack and implicitly with bank-angle modulation. Finally, the resulting trajectory is discussed in terms of g-loads, total range performances, and integral heat load absorbed, in the perspective of future manned exploration missions.
- 4 May 2022
- Published by IntechOpen
Open AccessLifting Entry Analysis for Manned Mars Exploration Missions
In the present work, a feasibility study of a manned Mars entry, descent, and landing mission, performed with a lifting vehicle, is analyzed. Mars entry challenges relate to different atmosphere models; consequently, the effective landing capability of a winged configuration is discussed. An entry trajectory study in the Martian atmosphere assuming both a planar and non-planar three degree-of-freedom model is performed. Peak heat rates and time-integrated heat loads during the descent are computed verifying the entry corridor. It is shown that prescribed aerodynamic performances can be modulated explicitly by varying angle of attack and implicitly with bank-angle modulation. Finally, the resulting trajectory is discussed in terms of g-loads, total range performances, and integral heat load absorbed, in the perspective of future manned exploration missions.
- 1 October 2021
- Published by Elsevier in Acta Astronautica
- Vol. 187, 141-155
Phase-A design of a reusable re-entry vehicle
- 1 October 2021
- Published by Elsevier in Acta Astronautica
- Vol. 187, 141-155
Phase-A design of a reusable re-entry vehicle
- 1 May 2021
- Published by Elsevier in Aerospace Science and Technology
- Vol. 112
An optimal heat-flux targeting procedure for LEO re-entry of reusable vehicles
- 1 May 2021
- Published by Elsevier in Aerospace Science and Technology
- Vol. 112
An optimal heat-flux targeting procedure for LEO re-entry of reusable vehicles
- 1 December 2020
- Published by Elsevier in Aerospace Science and Technology
- Vol. 107, 106303
Low speed longitudinal aerodynamics of a blended wing-body re-entry vehicle
- 1 December 2020
- Published by Elsevier in Aerospace Science and Technology
- Vol. 107, 106303
Low speed longitudinal aerodynamics of a blended wing-body re-entry vehicle