### Abstract

The flow field around a 6:1 prolate spheroid at angle of attack is predicted using solutions of the Reynolds-averaged Navier-Stokes equations and Detached-Eddy Simulation. The calculations were performed for the same conditions as measured by Chesnakas and Simpson^{1} and Wetzel et al.^{19} The Reynolds number is 4.2 × 10^{6}, the flow is tripped at x/L = 0.2, and the angle of attack α is varied from 10 to 20 degrees. RANS calculations are performed using the Spalart-Allmaras one-equation model10 (referred to as 'S-A' throughout). The influence of corrections to the S-A model accounting for streamline curvature and a non-linear constitutive relation are also considered. DES predictions are evaluated against the experimental measurements, RANS results, as well as calculationsperformed without an explicit turbulence model. In general, flow field predictions of the mean properties from the RANS and DES are similar. While initiated further along the spheroid compared to experimental measurements, predictions of primary and secondary separation agree reasonably well with measured values. Solutions of the flow obtained without any explicit turbulence model produce substantial errors in skin friction and pressure distributions.

Original language | English (US) |
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Title of host publication | 40th AIAA Aerospace Sciences Meeting and Exhibit |

State | Published - 2002 |

Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: Jan 14 2002 → Jan 17 2002 |

### Other

Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
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Country | United States |

City | Reno, NV |

Period | 1/14/02 → 1/17/02 |

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### ASJC Scopus subject areas

- Space and Planetary Science
- Aerospace Engineering

### Cite this

*40th AIAA Aerospace Sciences Meeting and Exhibit*

**Numerical investigation of flow past a prolate spheroid.** / Constantinescu, George S.; Pasinato, Hugo; Wang, You Qin; Squires, Kyle.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

*40th AIAA Aerospace Sciences Meeting and Exhibit.*40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States, 1/14/02.

}

TY - GEN

T1 - Numerical investigation of flow past a prolate spheroid

AU - Constantinescu, George S.

AU - Pasinato, Hugo

AU - Wang, You Qin

AU - Squires, Kyle

PY - 2002

Y1 - 2002

N2 - The flow field around a 6:1 prolate spheroid at angle of attack is predicted using solutions of the Reynolds-averaged Navier-Stokes equations and Detached-Eddy Simulation. The calculations were performed for the same conditions as measured by Chesnakas and Simpson1 and Wetzel et al.19 The Reynolds number is 4.2 × 106, the flow is tripped at x/L = 0.2, and the angle of attack α is varied from 10 to 20 degrees. RANS calculations are performed using the Spalart-Allmaras one-equation model10 (referred to as 'S-A' throughout). The influence of corrections to the S-A model accounting for streamline curvature and a non-linear constitutive relation are also considered. DES predictions are evaluated against the experimental measurements, RANS results, as well as calculationsperformed without an explicit turbulence model. In general, flow field predictions of the mean properties from the RANS and DES are similar. While initiated further along the spheroid compared to experimental measurements, predictions of primary and secondary separation agree reasonably well with measured values. Solutions of the flow obtained without any explicit turbulence model produce substantial errors in skin friction and pressure distributions.

AB - The flow field around a 6:1 prolate spheroid at angle of attack is predicted using solutions of the Reynolds-averaged Navier-Stokes equations and Detached-Eddy Simulation. The calculations were performed for the same conditions as measured by Chesnakas and Simpson1 and Wetzel et al.19 The Reynolds number is 4.2 × 106, the flow is tripped at x/L = 0.2, and the angle of attack α is varied from 10 to 20 degrees. RANS calculations are performed using the Spalart-Allmaras one-equation model10 (referred to as 'S-A' throughout). The influence of corrections to the S-A model accounting for streamline curvature and a non-linear constitutive relation are also considered. DES predictions are evaluated against the experimental measurements, RANS results, as well as calculationsperformed without an explicit turbulence model. In general, flow field predictions of the mean properties from the RANS and DES are similar. While initiated further along the spheroid compared to experimental measurements, predictions of primary and secondary separation agree reasonably well with measured values. Solutions of the flow obtained without any explicit turbulence model produce substantial errors in skin friction and pressure distributions.

UR - http://www.scopus.com/inward/record.url?scp=79953237820&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=79953237820&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:79953237820

BT - 40th AIAA Aerospace Sciences Meeting and Exhibit

ER -