1. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Side-view schematic of wind-tunnel arrangement

2. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Delta wing geometry

3. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Circumferentially averaged profiles of vortex perturbation field as a function of nondimensional radius from the vortex center (r/rc) (a) tangential velocity normalized by freestream velocity (Vθ/W∞), (b) streamwise velocity normalized by freestream velocity (Vz/W∞), (c) streamwise vorticity normalized by wing chord length and freestream velocity (ωzDi/W∞), and (d) flow angularity [α = tan-1(Vθ,max/Vz)]. N12 and N6 refer to the NACA 0012 wing with αvg = 12 deg and 6 deg, respectively. D12 and D6 refer to the delta wing with αvg = 12 deg and 6 deg.

4. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Vortex characteristics for centerline ingestion as a function of intake VR and normalized by unperturbed vortex measurements. NACA 0012 VG, αvg = 12 deg, Rec = 1.1 × 105. (a) Vortex centerline velocity magnitude (wc/wc,0), (b) vortex core radius (rc/rc,0), (c) peak tangential velocity (Vθ,max/Vθ,max,0), (d) peak streamwise vorticity (ωz,max/ωz,max,0), (e) average streamwise vorticity in vortex core (ωz,av/ωz,av,0), and (f) peak flow angle α* = (αmax/αmax,0).

5. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Vortex characteristics during centerline ingestion as a function of chord Reynolds number, and normalized by unperturbed vortex measurements. NACA 0012 VG,αvg = 12 deg, VR = 4.9–5.2. (a) Vortex centerline velocity magnitude (wc/wc,0), (b) vortex core radius (rc/rc,0), (c) peak tangential velocity (Vθ,max/Vθ,max,0), (d) peak streamwise vorticity (ωz,max/ωz,max,0), (e) average streamwise vorticity in vortex core (ωz,av/ωz,av,0), and (f) peak flow angle α* = (αmax/αmax,0)[αmax = max(tan-1(Vθ/Vz))]. Note that Rev,0 = 2.4 × 104.

6. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Vortex characteristics during centerline ingestion, as a function of intake VR for centerline (CL) and off-axis (OA) ingestion, and normalized by unperturbed vortex measurements. NACA 0012 VG, αvg = 12 deg, VR = 10.3 and (a) Vortex centerline velocity magnitude (wc/wc,0), (b) vortex core radius (rc/rc,0), (c) peak tangential velocity (Vθ,max/Vθ,max,0), (d) peak streamwise vorticity (ωz,max/ωz,max,0), (e) average streamwise vorticity in vortex core (ωz,av/ωz,av,0), and (f) peak flow angle α* = (αmax/αmax,0)[αmax = max(tan-1(Vθ/Vz))].

7. Date of download: 12/24/2017
Copyright © ASME. All rights reserved.
From: The Effect of Streamtube Contraction on the Characteristics of a Streamwise Vortex
J. Fluids Eng. 2015;137(6): doi: /
Figure Legend:
Vortex characteristics during centerline ingestion, NACA 0012 and delta wing VG, αvg = 12 deg and 6 deg, VR = 4.9, and normalized by unperturbed vortex measurements, where Rev,0 = 2.4 × 104, (a) vortex centerline velocity magnitude (wc/wc,0), (b) vortex core radius (rc/rc,0), (c) peak tangential velocity (Vθ,max/Vθ,max,0), (d) peak streamwise vorticity (ωz,max/ωz,max,0), (e) average streamwise vorticity in vortex core (ωz,av/ωz,av,0), and (f) peak flow angle α* = (αmax/αmax,0)[αmax = max(tan-1(Vθ/Vz))]. Note that Rev,0 = 2.4 × 104.