Methods to Scale Subsonic Wind Tunnel Data to Full-Scale

2012 ◽  
Author(s):  
Balaji Kaushik ◽  
Willem Anemaat
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Subsonic Wind Tunnel ◽  
Wind Tunnel Data

Evaluation of the Wright 1901 Glider Using Full-Scale Wind-Tunnel Data

2003 ◽  
Vol 40 (3) ◽  
pp. 417-424 ◽  
Author(s):  
Kevin Kochersberger ◽  
Robert Ash ◽  
Ash Britcher ◽  
Drew Landman ◽  
Ken Hyde
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Wind Tunnel Data

scholarly journals Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel

2018 ◽  
Vol 30 (4) ◽  
pp. 457-463
Author(s):  
Karolina Krajček Nikolić ◽  
Anita Domitrović ◽  
Slobodan Janković
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Internal Force ◽  
Force Balance ◽  
Wind Tunnels ◽  
Subsonic Wind Tunnel ◽  
Lower Reynolds Number ◽  
Scaling Methods ◽  
Reynolds Number Effects ◽  
Wind Tunnel Data

To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited  usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.

Comparison of RANS and Detached Eddy Simulation Results to Wind-Tunnel Data for the Surface Pressures Upon a Class 43 High-Speed Train

2015 ◽  
Vol 137 (4) ◽  
Author(s):  
Justin A. Morden ◽  
Hassan Hemida ◽  
Chris. J. Baker
Keyword(s):  
Wind Tunnel ◽  
Surface Pressure ◽  
High Speed ◽  
Model Comparison ◽  
Computational Cost ◽  
Full Scale ◽  
Cost Comparison ◽  
Detached Eddy Simulation ◽  
Eddy Simulation ◽  
Wind Tunnel Data

Currently, there are three different methodologies for evaluating the aerodynamics of trains; full-scale measurements, physical modeling using wind-tunnel, and moving train rigs and numerical modeling using computational fluid dynamics (CFD). Moreover, different approaches and turbulence modeling are normally used within the CFD framework. The work in this paper investigates the consistency of two of these methodologies; the wind-tunnel and the CFD by comparing the measured surface pressure with the computed CFD values. The CFD is based on Reynolds-Averaged Navier–Stokes (RANS) turbulence models (five models were used; the Spalart–Allmaras (S–A), k-ε, k-ε re-normalization group (RNG), realizable k-ε, and shear stress transport (SST) k-ω) and two detached eddy simulation (DES) approaches; the standard DES and delayed detached eddy simulation (DDES). This work was carried out as part of a larger project to determine whether the current methods of CFD, model scale and full-scale testing provide consistent results and are able to achieve agreement with each other when used in the measurement of train aerodynamic phenomena. Similar to the wind-tunnel, the CFD approaches were applied to external aerodynamic flow around a 1/25th scale class 43 high-speed tunnel (HST) model. Comparison between the CFD results and wind-tunnel data were conducted using coefficients for surface pressure, measured at the wind-tunnel by pressure taps fitted over the surface of the train in loops. Four different meshes where tested with both the RANS SST k-ω and DDES approaches to form a mesh sensitivity study. The four meshes featured 18, 24, 34, and 52 × 106 cells. A mesh of 34 × 106 cells was found to provide the best balance between accuracy and computational cost. Comparison of the results showed that the DES based approaches; in particular, the DDES approach was best able to replicate the wind-tunnel results within the margin of uncertainty.

Evaluation of the Wright 1902 Glider Using Full-Scale Wind-Tunnel Data

2005 ◽  
Vol 42 (3) ◽  
pp. 710-717 ◽  
Author(s):  
K. B. Kochersberger ◽  
D. Landman ◽  
J. L. Player ◽  
K. W. Hyde
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Wind Tunnel Data

OPTIMUM FULL-SCALE SUBSONIC WIND TUNNEL

1986 ◽  
Author(s):  
K. MORT ◽  
P. SODERMAN ◽  
L. MEYN
Keyword(s):  
Wind Tunnel ◽  
Full Scale ◽  
Subsonic Wind Tunnel
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