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