..30.2: tabs in Langley 4 x 7 m*
MARTIN, R.M.; BROOKS, T.F.; HOAD, D.R.*
Reduction of background noise induced by wind tunnel jet exit vanes*
AIAA J. 23, 1631*
1985. `
..30.1: Lewis thick vanes - loss 0 . 12 compared to 0 . 14 for thin vanes*
GELDER, T.F.; MOORE,  R.D.; SANZ, J.M.; McFARLAND, E.R.*
Wind tunnel turning vanes of modern design*
AIAA-86-0044, NASA-TM-87416*
1986. `
..30.2:  suction side pressure distribution same as a Wortmann low-Re aerofoil - gap/chord 0 . 61.  Pressure-drop coefficient 0 . 036 in 2D, 0 . 048 overall (end wall BLs look a mess)*
SAHLIN, A.; JOHANSSON, A.V.*
Design of guide vanes for minimizing the pressure loss in sharp bends*
Phys. Fluids A3, 1934*
1991. `
..30.2: turbulence and noise issues, for transition work. Put heat exchanger in the corner vanes*
RESHOTKO, E.; SARIC, W.S.; NAGIB, H.M.*
Flow quality issues for large wind tunnels*
AIAA 97-0225*
1997. `
..30.2:  pressure-loss coefficient as low as 0.041 with expansion ratio 4/3.  About 5 percent thick, 90 deg. included angle*
LINDGREN, B.; OSTERLUND, J.; JOHANSSON, A.V.*
Measurement and calculation of guide vane performance in expanding bends for wind-tunnels*
Expts. in Fluids 24, 265*
1998.`
..30.3:  2D CFD (k, eps.) used as a guide.  Semi-circular bends and no diffuser - low velocity on outside of bend*
GORDON, R.; IMBABI, M.S.*
CFD simulation and experimental validation of a new closed circuit wind/water tunnel design*
J. Fluids Engg. 120, 311*
1998. `