Analysis of propeller performance with a modular blade element momentum method
Analysis of propeller performance with a modular blade element momentum method
Accurate, low‑cost prediction tools are essential for the rapid sizing and optimisation of propellers used in emerging electric‑propulsion architectures. The current work extends the classical Blade Element Momentum Theory (BEMT) through a modular suite of aerodynamic corrections that account for (i) three‑dimensional rotational augmentation, (ii) compressibility effects at moderate tip‑Mach numbers and (iii) post‑stall behaviour via a smoothed Viterna polar extrapolation. The framework is investigated on two different test cases, a four‑blade Beaver propeller and a two‑blade APC 10×7 propeller, over advance ratio ranges representative of hover, climb and cruise of an eVTOL. Validations against experiment data have shown that the full correction set reduces mean absolute errors in thrust and torque coefficients from around 18% down to 6% across J from 0.6 to 1.0 for the APC~10×7 propeller. A detailed sensitivity study demonstrates that inappropriate aerofoil polars (e.g.\ NACA~0012) can distort integral performance by more than 25% and alter spanwise loading trends qualitatively; the proposed Viterna blending routine reduces the potential issue caused by out-of-range polar by enforcing physically consistent lift and drag characteristics for the AoA up to $\pm90^{\circ}$. The work therefore delivers (i) an extensible, open‑source BEMT implementation, (ii) a robust polar extension technique and (iii) a comprehensive validation dataset that may serve as a benchmark for future mid‑fidelity propeller models. These contributions support the reliable application of BEMT to distributed propulsion and eVTOL design studies where hundreds of operating points must be evaluated in real time.
Aerodynamic Characteristics, Aerodynamic Performance, Blade Element Momentum Theory, Compressibility Effect, Counter Rotating Propellers, Distributed Electric Propulsion, Dynamic Pressure, Electric Vertical Take off and Landing, Propulsive Efficiency, Thin Airfoil Theory
Li, Zhuoneng
bd8601a6-add5-44d0-9867-b6451ef7a87d
Da Ronch, Andrea
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
16 July 2025
Li, Zhuoneng
bd8601a6-add5-44d0-9867-b6451ef7a87d
Da Ronch, Andrea
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Li, Zhuoneng and Da Ronch, Andrea
(2025)
Analysis of propeller performance with a modular blade element momentum method.
In AIAA Aviation Forum and Ascend 2025.
AIAA International..
(doi:10.2514/6.2025-3094).
Record type:
Conference or Workshop Item
(Paper)
Abstract
Accurate, low‑cost prediction tools are essential for the rapid sizing and optimisation of propellers used in emerging electric‑propulsion architectures. The current work extends the classical Blade Element Momentum Theory (BEMT) through a modular suite of aerodynamic corrections that account for (i) three‑dimensional rotational augmentation, (ii) compressibility effects at moderate tip‑Mach numbers and (iii) post‑stall behaviour via a smoothed Viterna polar extrapolation. The framework is investigated on two different test cases, a four‑blade Beaver propeller and a two‑blade APC 10×7 propeller, over advance ratio ranges representative of hover, climb and cruise of an eVTOL. Validations against experiment data have shown that the full correction set reduces mean absolute errors in thrust and torque coefficients from around 18% down to 6% across J from 0.6 to 1.0 for the APC~10×7 propeller. A detailed sensitivity study demonstrates that inappropriate aerofoil polars (e.g.\ NACA~0012) can distort integral performance by more than 25% and alter spanwise loading trends qualitatively; the proposed Viterna blending routine reduces the potential issue caused by out-of-range polar by enforcing physically consistent lift and drag characteristics for the AoA up to $\pm90^{\circ}$. The work therefore delivers (i) an extensible, open‑source BEMT implementation, (ii) a robust polar extension technique and (iii) a comprehensive validation dataset that may serve as a benchmark for future mid‑fidelity propeller models. These contributions support the reliable application of BEMT to distributed propulsion and eVTOL design studies where hundreds of operating points must be evaluated in real time.
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Published date: 16 July 2025
Venue - Dates:
AIAA AVIATION FORUM AND ASCEND 2025, , Las Vegas, United States, 2025-07-21 - 2025-07-25
Keywords:
Aerodynamic Characteristics, Aerodynamic Performance, Blade Element Momentum Theory, Compressibility Effect, Counter Rotating Propellers, Distributed Electric Propulsion, Dynamic Pressure, Electric Vertical Take off and Landing, Propulsive Efficiency, Thin Airfoil Theory
Identifiers
Local EPrints ID: 504561
URI: http://eprints.soton.ac.uk/id/eprint/504561
PURE UUID: c71d7b38-04a8-4c81-9e4d-b91974a6732c
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Date deposited: 15 Sep 2025 16:43
Last modified: 18 Oct 2025 01:47
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Author:
Zhuoneng Li
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