High-quality zero-lift drag data from NACA TR-1160 Cases include transonic-supersonic Mach numbers with weak viscous/inviscid interaction Motivation for elliptic solve was viscous correction for general geometries Use in “single-pass” mode is essentially free NACA RM-10 A posteriori viscous corrections 1.8 M cells
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High-quality zero-lift drag data from NACA TR-1160
Cases include transonic-supersonic Mach numbers with weak viscous/inviscid interaction
Motivation for elliptic solve was viscous correction for general geometries
Use in “single-pass” mode is essentially free
NACA RM-10A posteriori viscous corrections
1.8 M cells
NACA RM-10Mach sweep, M∞ = 0.8-2.5 @ α = 0°
Density Contours
All cases converged in under 200 multigrid cycles, ~2 CPU hrs/case
NACA RM-10Mach sweep, M∞ = 0.8-2.5 @ α = 0°
Boundary-layer loops on RM-10
NACA RM-10Mach sweep, M∞ = 0.8 – 2.5, ReD = 35x106 – 140x106, α = 0°
Good agreement for both axial force and skin-friction estimates
Single-pass estimate is extremely cheap & robustNo base correction for power off
1 1.5 2 2.5Mach Number
0.00
0.05
0.10
0.15
0.20
0.25A
xial
For
ce C
oef.
Flight Test, NACA 1160, fig 9aCart3D - InviscidCart3D - Inviscid + IBLCx visc
1 1.5 2 2.5Mach Number
0.00
0.05
0.10
0.15
0.20
0.25A
xial
For
ce C
oef.
Flight Test, NACA 1160, fig 9aCart3D - InviscidCart3D - Inviscid + IBLCx visc
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