Numerical investigation of flow past a prolate spheroid

George S. Constantinescu, Hugo Pasinato, You Qin Wang, Kyle Squires

Research output: Chapter in Book/Report/Conference proceedingConference contribution

7 Citations (Scopus)

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 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.

Original languageEnglish (US)
Title of host publication40th AIAA Aerospace Sciences Meeting and Exhibit
StatePublished - 2002
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: Jan 14 2002Jan 17 2002

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period1/14/021/17/02

Fingerprint

prolate spheroids
angle of attack
turbulence models
Angle of attack
Turbulence models
flow field
Flow fields
flow distribution
prediction
predictions
turbulence
skin friction
Skin friction
spheroids
Navier-Stokes equations
pressure distribution
Reynolds number
Pressure distribution
Navier-Stokes equation
Navier Stokes equations

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Constantinescu, G. S., Pasinato, H., Wang, Y. Q., & Squires, K. (2002). Numerical investigation of flow past a prolate spheroid. In 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.

40th AIAA Aerospace Sciences Meeting and Exhibit. 2002.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Constantinescu, GS, Pasinato, H, Wang, YQ & Squires, K 2002, Numerical investigation of flow past a prolate spheroid. in 40th AIAA Aerospace Sciences Meeting and Exhibit. 40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States, 1/14/02.
Constantinescu GS, Pasinato H, Wang YQ, Squires K. Numerical investigation of flow past a prolate spheroid. In 40th AIAA Aerospace Sciences Meeting and Exhibit. 2002
Constantinescu, George S. ; Pasinato, Hugo ; Wang, You Qin ; Squires, Kyle. / Numerical investigation of flow past a prolate spheroid. 40th AIAA Aerospace Sciences Meeting and Exhibit. 2002.
@inproceedings{62a29c42e1604c23ad793d7ab16c7565,
title = "Numerical investigation of flow past a prolate spheroid",
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 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.",
author = "Constantinescu, {George S.} and Hugo Pasinato and Wang, {You Qin} and Kyle Squires",
year = "2002",
language = "English (US)",
booktitle = "40th AIAA Aerospace Sciences Meeting and Exhibit",

}

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 -