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arxiv: 2510.22470 · v1 · submitted 2025-10-26 · ⚛️ physics.flu-dyn

Numerical Investigation of Discontinuous Ice Effects on Swept Wings

Jiawei Chen , Maochao Xiao , Ziyu Zhou , Yufei Zhang This is my paper

Pith reviewed 2026-05-18 04:59 UTC · model grok-4.3

classification ⚛️ physics.flu-dyn
keywords discontinuous iceswept wingslift reductiongap jetsvortex sheddingStrouhal numberaerodynamic performancedetached-eddy simulation
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0 comments X

The pith

Discontinuous ice on swept wings reduces lift more than continuous ice by disrupting vortices with gap jets.

A machine-rendered reading of the paper's core claim, the machinery that carries it, and where it could break.

The paper compares aerodynamic effects of clean, continuous-ice, and discontinuous-ice configurations on infinite swept wings using numerical simulation. It establishes that gaps in the ice create jets which break up leading-edge vortices, producing larger lift losses than a solid ice layer while incurring a smaller drag increase and avoiding abrupt stall. A sympathetic reader would care because aircraft performance in icing conditions directly affects safety margins, and these differences suggest that partial ice coverage can be more hazardous than uniform coverage in some respects.

Core claim

Discontinuous ice causes a more severe reduction in lift than continuous ice. Continuous ice forms a large separation bubble that helps maintain lift, while discontinuous ice disrupts leading-edge vortex formation through gap jets, resulting in greater lift loss but a smaller drag penalty. The discontinuous-ice wing does not exhibit a sudden stall-induced lift drop. Its flow is characterized by a separating shear layer and Kármán vortex shedding that becomes irregular due to gap jets, with three chord-based Strouhal numbers identified at 11.3, 22.6, and 33.9.

What carries the argument

Gap jets formed between segments of discontinuous ice that interfere with leading-edge vortex formation and create irregular shear layers.

If this is right

  • Discontinuous ice produces greater lift loss but smaller drag penalty than continuous ice at the same conditions.
  • The discontinuous-ice configuration avoids the sudden lift drop associated with stall on continuous-ice wings.
  • Lift and drag fluctuations occur mainly at twice the vortex-shedding frequency because of the gap jets.
  • The separating shear layer becomes irregular specifically due to interference from the gap jets.

Where Pith is reading between the lines

These are editorial extensions of the paper, not claims the author makes directly.

  • Partial ice removal or de-icing that leaves gaps could sometimes worsen lift performance compared with leaving the ice in place.
  • The higher Strouhal number when scaled by ice width suggests gap jets create a more energetic wake than a simple cylinder.
  • Design of ice-protection systems might need to account for gap-induced unsteady loads in addition to mean aerodynamic penalties.

Load-bearing premise

The artificially simulated discontinuous ice shapes and the enhanced delayed detached-eddy simulation accurately capture real ice accretion and the unsteady three-dimensional flows on swept wings.

What would settle it

Wind-tunnel measurements of lift, drag, and surface pressures on a physical swept-wing model with naturally accreted or precisely replicated discontinuous ice at the same angles of attack would directly test the reported lift reductions and Strouhal numbers.

read the original abstract

This study investigates the aerodynamic performance and flow structures of infinite swept wings with artificially simulated discontinuous ice using an enhanced delayed detached-eddy simulation. Comparisons are made among clean, continuous-ice, and discontinuous-ice configurations. Results show that discontinuous ice causes a more severe reduction in lift than continuous ice. While continuous ice forms a large separation bubble that helps maintain lift, discontinuous ice disrupts leading-edge vortex formation through gap jets, resulting in greater lift loss but a smaller drag penalty. Unlike the continuous-ice wing, the discontinuous-ice case does not exhibit a sudden stall-induced lift drop. The flow over the discontinuous-ice wing can be characterized by two canonical patterns: a separating shear layer and K\'arm\'an vortex shedding. However, the separating shear layer becomes irregular due to the interference of gap jets. Three characteristic chord-based Strouhal numbers (St)-11.3, 22.6, and 33.9-are identified. The lowest (St=11.3) corresponds to the shedding of vortex pairs; when nondimensionalized by the ice width, it yields St = 0.58, which is higher than that of a canonical cylinder wake. Furthermore, lift and drag fluctuations occur predominantly at St = 22.6, twice the shedding frequency, primarily induced by the gap jets-a phenomenon absent in the continuous-ice case.

Editorial analysis

A structured set of objections, weighed in public.

Desk editor's note, referee report, simulated authors' rebuttal, and a circularity audit. Tearing a paper down is the easy half of reading it; the pith above is the substance, this is the friction.

Referee Report

3 major / 2 minor

Summary. The manuscript numerically investigates the aerodynamic performance and flow structures of infinite swept wings with artificially simulated discontinuous ice using enhanced delayed detached-eddy simulation (ED-DES). It compares clean, continuous-ice, and discontinuous-ice configurations and claims that discontinuous ice causes a more severe reduction in lift than continuous ice. Continuous ice forms a large separation bubble that helps maintain lift, while discontinuous ice disrupts leading-edge vortex formation through gap jets, yielding greater lift loss but a smaller drag penalty and no sudden stall-induced lift drop. The flow over the discontinuous-ice wing exhibits separating shear layers and Kármán vortex shedding, with three characteristic chord-based Strouhal numbers (11.3, 22.6, 33.9) identified; lift and drag fluctuations occur predominantly at St = 22.6 due to gap jets.

Significance. If the ED-DES predictions prove accurate, the results would advance understanding of three-dimensional unsteady interactions on iced swept wings by contrasting the effects of continuous versus discontinuous ice accretion. The detailed characterization of gap-jet interference with vortex formation, the absence of sudden stall in the discontinuous case, and the specific Strouhal numbers (including the ice-width-normalized value of 0.58) provide concrete, falsifiable observations on force fluctuations and flow patterns that could inform icing-related aerodynamic modeling.

major comments (3)
  1. [Abstract] Abstract: The central comparative claim that discontinuous ice produces more severe lift reduction than continuous ice (via gap-jet disruption of leading-edge vortices versus a stabilizing separation bubble) is not anchored by any reported validation against icing-tunnel or flight-test data at the relevant sweep and Reynolds number; without such anchoring the lift-ordering result remains conditional on the specific numerical idealization.
  2. [Methods/Results] Methods/Results: No sensitivity study is presented on the artificial discontinuous-ice parameters (gap width, protrusion height, or spanwise periodicity) that control the gap-jet momentum and vortex coherence; because these parameters are imposed rather than grown from an icing model, their variation could alter the reported lift penalty and the identified flow patterns.
  3. [Results] Results: Mesh-convergence data and uncertainty quantification for the lift, drag, and Strouhal-number predictions are absent, which directly affects confidence in the quantitative differences in stall behavior and the claim that fluctuations occur at twice the shedding frequency due to gap jets.
minor comments (2)
  1. [Abstract] Abstract: The definition of the Strouhal number when nondimensionalized by ice width (yielding St = 0.58) should be stated explicitly and compared to literature values for cylinder wakes to strengthen the interpretation.
  2. Ensure consistent first-use definition of acronyms (ED-DES, DDES) and clarify whether the reported Kármán vortex shedding is spanwise or streamwise in the discontinuous-ice case.

Simulated Author's Rebuttal

3 responses · 1 unresolved

We thank the referee for the constructive and detailed comments on our numerical study of discontinuous ice on swept wings. We address each major comment point by point below, with honest indications of where revisions will be incorporated.

read point-by-point responses

  1. Referee: [Abstract] Abstract: The central comparative claim that discontinuous ice produces more severe lift reduction than continuous ice (via gap-jet disruption of leading-edge vortices versus a stabilizing separation bubble) is not anchored by any reported validation against icing-tunnel or flight-test data at the relevant sweep and Reynolds number; without such anchoring the lift-ordering result remains conditional on the specific numerical idealization.

    Authors: Our investigation is a high-fidelity numerical study employing ED-DES on infinite swept wings. The reported lift reduction ordering and associated flow mechanisms (gap jets disrupting leading-edge vortices in the discontinuous case versus a stabilizing separation bubble in the continuous case) are direct outcomes of the simulated flow fields under identical numerical conditions. We agree that the quantitative results are conditional on the numerical idealizations and lack direct experimental anchoring at the exact sweep and Reynolds number. In the revised manuscript we will explicitly qualify the abstract and discussion sections to emphasize the computational nature of the findings and the physical mechanisms identified, while noting the desirability of future experimental validation. revision: partial

  2. Referee: [Methods/Results] Methods/Results: No sensitivity study is presented on the artificial discontinuous-ice parameters (gap width, protrusion height, or spanwise periodicity) that control the gap-jet momentum and vortex coherence; because these parameters are imposed rather than grown from an icing model, their variation could alter the reported lift penalty and the identified flow patterns.

    Authors: The discontinuous-ice geometry parameters were chosen to represent typical values drawn from icing literature for swept-wing accretion, enabling the formation of gap jets while remaining computationally tractable. A comprehensive sensitivity study on gap width, protrusion height, and periodicity was not performed owing to the substantial cost of additional ED-DES runs. We will add a paragraph in the methods section of the revised manuscript that explains the parameter selection rationale and qualitatively discusses expected sensitivities of the gap-jet momentum and vortex coherence based on our preliminary observations. revision: partial

  3. Referee: [Results] Results: Mesh-convergence data and uncertainty quantification for the lift, drag, and Strouhal-number predictions are absent, which directly affects confidence in the quantitative differences in stall behavior and the claim that fluctuations occur at twice the shedding frequency due to gap jets.

    Authors: Grid-independence checks were conducted during the simulation campaign to confirm adequate resolution of the separating shear layers, gap jets, and vortex shedding. Detailed convergence data were not reported in the original manuscript. We will include a new subsection (or appendix) in the revised version that presents mesh-convergence results for lift and drag coefficients together with the extracted Strouhal numbers, along with a brief statement on numerical uncertainty derived from the observed variations across grids. revision: yes

standing simulated objections not resolved
  • Direct experimental validation of the lift-reduction ordering and Strouhal-number values at the specific sweep and Reynolds number, which would require new icing-tunnel or flight-test data beyond the scope of this numerical investigation.

Circularity Check

0 steps flagged

No significant circularity in direct CFD simulation outputs

full rationale

The paper reports aerodynamic coefficients, flow structures, and Strouhal numbers obtained by solving the unsteady Navier-Stokes equations with an enhanced delayed detached-eddy simulation turbulence closure on fixed, artificially imposed ice geometries. These quantities are direct numerical outputs, not parameters fitted to the simulation data and then re-labeled as predictions, nor self-defined quantities. No load-bearing self-citations, uniqueness theorems, or ansatzes imported from prior author work appear in the derivation chain. The central comparative claims (discontinuous ice producing greater lift loss via gap-jet disruption) follow from the computed solutions without reduction to the inputs by construction.

Axiom & Free-Parameter Ledger

0 free parameters · 1 axioms · 0 invented entities

The central claims rest on the fidelity of the chosen turbulence model and the idealized ice geometries; no new physical entities are introduced and no free parameters are explicitly fitted within the reported results.

axioms (1)
  • domain assumption Enhanced delayed detached-eddy simulation accurately captures the unsteady separated flow and vortex shedding induced by ice geometries on swept wings.
    This modeling choice underpins all reported flow structures, lift/drag differences, and Strouhal number identifications.

pith-pipeline@v0.9.0 · 5775 in / 1278 out tokens · 37891 ms · 2026-05-18T04:59:14.728310+00:00 · methodology

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Reference graph

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