TY - GEN
T1 - Numerical Investigation of Drag Characteristics on Wing Planform NASA 20612
AU - Putro, Setyo Hariyadi Suranto
AU - Junipitoyo, Bambang
AU - Sutardi,
AU - Widodo, Wawan Aries
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.
PY - 2025
Y1 - 2025
N2 - The drag characteristics of a wing greatly affect the aerodynamic performance of the aircraft as a whole. This is because the aircraft movement process is controlled by the wing. The use of different airfoils and wing planforms will produce different drag characteristics. The numerical simulation in this study uses the NASA 20612 airfoil used on the Embraer 145 aircraft with three forms of planform wing, namely rectangular, delta, and swept back wing. The turbulent model used is k–ε Realizable with Re = 2.88 × 107. In the rectangular wing, the vorticity is centered on the area behind the wingtip while the delta and swept back wing are partially centered on the area behind the midspan. This shows that the wing planform greatly affects the formation of vorticity which in turn affects the induced drag formed. In the rectangular wing, the separation occurs early in the midspan area while in the delta and swept back wing it is closer to the wingtip area. At the wingtip, delta, and swept-back wings have less tip vortex effect than rectangular wings. This shows that the use of delta and swept-back wings can reduce the occurrence of induced drag on the wing airfoil NACA 20612.
AB - The drag characteristics of a wing greatly affect the aerodynamic performance of the aircraft as a whole. This is because the aircraft movement process is controlled by the wing. The use of different airfoils and wing planforms will produce different drag characteristics. The numerical simulation in this study uses the NASA 20612 airfoil used on the Embraer 145 aircraft with three forms of planform wing, namely rectangular, delta, and swept back wing. The turbulent model used is k–ε Realizable with Re = 2.88 × 107. In the rectangular wing, the vorticity is centered on the area behind the wingtip while the delta and swept back wing are partially centered on the area behind the midspan. This shows that the wing planform greatly affects the formation of vorticity which in turn affects the induced drag formed. In the rectangular wing, the separation occurs early in the midspan area while in the delta and swept back wing it is closer to the wingtip area. At the wingtip, delta, and swept-back wings have less tip vortex effect than rectangular wings. This shows that the use of delta and swept-back wings can reduce the occurrence of induced drag on the wing airfoil NACA 20612.
KW - Drag
KW - NASA 20612
KW - Separation
KW - Vorticity
KW - Wing planform
UR - https://www.scopus.com/pages/publications/105019641844
U2 - 10.1007/978-981-96-5063-7_24
DO - 10.1007/978-981-96-5063-7_24
M3 - Conference contribution
AN - SCOPUS:105019641844
SN - 9789819650620
T3 - Lecture Notes in Mechanical Engineering
SP - 295
EP - 308
BT - Proceedings of the 10th International Conference and Exhibition on Sustainable Energy and Advanced Materials - ICE-SEAM 2024, Surakarta, Indonesia Proceedings of the 10th International Conference and Exhibition on Sustainable Energy and Advanced Materials - ICE-SEAM 2024
A2 - Raharjo, Wahyu Purwo
A2 - Imaduddin, Fitrian
A2 - Smaradhana, Dharu Feby
PB - Springer Science and Business Media Deutschland GmbH
T2 - 10th International Conference and Exhibition on Sustainable Energy and Advanced Materials, ICE-SEAM 2024
Y2 - 19 September 2024 through 20 September 2024
ER -