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Compressible flow in front of an axisymmetric blunt object: analytic approximation and astrophysical implications
Earth and Planetary Astrophysics · Submitted 18 Nov 2016
abstract compiled · 2026-09-23 · no language-model review
The authors' main claim We show that the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity.
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The abstract, sentence by sentence
Compressible flows around blunt objects have diverse applications, but current analytic treatments are inaccurate and limited to narrow parameter regimes. We show that the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity. This reproduces both subsonic and supersonic flows measured and simulated for a sphere, including the transonic regime and the bow shock properties. Some astrophysical implications are outlined, in particular for planets in the solar wind and for clumps and bubbles in the intergalactic medium. The bow shock standoff distance normalized by the obstacle curvature is $\sim 2/(3g)$ in the strong shock limit, where $g$ is the compression ratio. For a subsonic Mach number $M$ approaching unity, the thickness $\delta$ of an initially weak, draped magnetic layer is a few times larger than in the incompressible limit, with amplification $\sim ({1+1.3M^{2.6}})/({3\delta})$.
background contribution method result interpretation main claim
| # | sentence | role | the authors' own work | states the main conclusion | strength |
|---|---|---|---|---|---|
| s0 | Compressible flows around blunt objects have diverse applications, but current analytic treatments are inaccurate and limited to narrow parameter regimes. | gap 0.63 | 0.04 | 0.04 | asserted 1.00 |
| s1 | We show that the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity. | contribution 0.74 | 0.97 | 0.85 | asserted 1.00 |
| s2 | This reproduces both subsonic and supersonic flows measured and simulated for a sphere, including the transonic regime and the bow shock properties. | result 0.98 | 0.77 | 0.26 | asserted 1.00 |
| s3 | Some astrophysical implications are outlined, in particular for planets in the solar wind and for clumps and bubbles in the intergalactic medium. | interpretation 0.97 | 0.67 | 0.04 | asserted 0.65 |
| s4 | The bow shock standoff distance normalized by the obstacle curvature is $\sim 2/(3g)$ in the strong shock limit, where $g$ is the compression ratio. | result 1.00 | 0.87 | 0.10 | asserted 1.00 |
| s5 | For a subsonic Mach number $M$ approaching unity, the thickness $\delta$ of an initially weak, draped magnetic layer is a few times larger than in the incompressible limit, with amplification $\sim ({1+1.3M^{2.6}})/({3\delta})$. | result 1.00 | 0.82 | 0.06 | asserted 1.00 |
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The paper
Original abstract
Compressible flows around blunt objects have diverse applications, but current analytic treatments are inaccurate and limited to narrow parameter regimes. We show that the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity. This reproduces both subsonic and supersonic flows measured and simulated for a sphere, including the transonic regime and the bow shock properties. Some astrophysical implications are outlined, in particular for planets in the solar wind and for clumps and bubbles in the intergalactic medium. The bow shock standoff distance normalized by the obstacle curvature is $\sim 2/(3g)$ in the strong shock limit, where $g$ is the compression ratio. For a subsonic Mach number $M$ approaching unity, the thickness $\delta$ of an initially weak, draped magnetic layer is a few times larger than in the incompressible limit, with amplification $\sim ({1+1.3M^{2.6}})/({3\delta})$.
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