..30.2:Ames 12 ft and Langley 8ft (no screens - worse) - both poor near M=1*
HARVEY, W.D.; STAINBACK, P.C.; OWEN, F.K.*
Evaluation of flow quality in two large NASA wind tunnels at transonic speeds*
NASA TP 1737 and J. Aircraft 18, 451, 1981*
1980. `
..30.2: apparently, bad advice to put screen ahead of honeycomb*
McKINNEY, M.O.; SHEIMAN, J.*
Evaluation of turbulence reduction devices for the Langley 8-ft transonic pressure tunnel*
NASA TM 81792*
1981. `
..30.2: part-model tests*
GENTRY, G.L.; IGOE, W.B.; FULLER, D.E.*
Description of 0.186 scale model of high-speed duct of National Transonic facility*
NASA TM 81949*
1981. `
..30.3:interesting but plausible flow angles at contraction exit*
MOREL, J.P.*
The ETW European transonic wind tunnel project - progress report*
ONERA T.P. 1981-121*
1981. `
..30.2:computer loop, iterating Hilbert corrections to wall shape*
GOODYER, M.J.; WOLF, S.W.D.*
Development of a self-streamlining flexible walled transonic test section*
AIAA J. 20, 227*
1982. `
..30.2: God, motherhood etc for transonic tunnels. The topics are integrated*
STEINLE, F.; STANEWSKY, E.*
Wind tunnel flow quality and data accuracy requirements*
AGARD Adv. Rept. 184*
1982. `
..30.2,16.2: GARTEUR - mainly tunnel interference*
GARTEUR*
Two dimensional transonic testing methods*
NLR TR 83086L*
1983. `

..30.2:refers to WALINT panel method*
MABEY, D.G.; STEINIE, F.W.*
Computer studies of hybrid slotted working sections with minimum steady interference at subsonic speeds*
Aero. J. 89, 135*
1985. `
..30.1: cryogenic*
HOLMES, H.K.*
Model measurements in the National Transonic Facility*
Presented at llth ICIASF, Stanford, p. 1*
1985. `
..30.1: 6 atm, M= 0 . 9, 80K*
JOHNSON, W.G.*
High Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-meter transonic cryogenic tunnel*
NASA TM 86371*
1985. `
..30.2: good indication of when shocks reach tunnel wall*
MUNDELL, A.R.G.; MABEY, D.G.*
Pressure fluctuations caused by transonic shock/boundary-layer interaction*
RAE TM 2047*
1985. `
..30.1: worries about changes in LN2 feed rate*
JOHNSON, C.B.; STAINBACK, P.C.*
Dynamic measurement of total temperature, pressure and velocity in the Langley 0.3-meter transonic cryogenic tunnel*
NASA TP 2584*
1986. `
..30.3: first pilot tunnel*
LADSON, C.L.; RAY, E.J.*
Evolution, calibration and operational characteristics of the two-dimensional test section of the Langley 0.3 m transonic cryogenic tunnel*
NASA TP 2741*
1987. `
..30.3: short description for prospective users*
PUFFERT-MEISSNER, W.*
The transonic wind tunnel (TWB) at DFVLR in Braunschweig*
DFVLR-Mitt. 88-01*
1988. `
..30.2,25.7: optimization procedure to correct M and alpha*
RIZK, M.H.; LOVELL, D.R.; BAKER, T.J.*
Euler procedure for correcting two-dimensional transonic wind-tunnel wall interference*
AIAA J. 26, 1457*
1988. `
..30.3,24.4,18.2: mainly hypersonics*
BECKWITH, I.E.; MILLER, C.G.*
Aerothermodynamics and transition in high-speed wind tunnels at NASA Langley*
Ann. Rev. Fluid Mech. 22, 419*
1990. `
..30.2: Langley 0 . 3m TCT - 0 . 7 percent rms vel. and some plenum reasonances*
NG, W.F.; GUNDAPPA, M.; GRIFFITH, D.O.; PETERSON, J.B.*
Turbulence measurements and noise generation in a transonic cryogenic wind tunnel*
AIAA J. 28, 853*
1990. `
..30.1:  accurate prediction of condensation is essential*
WEGENER, P.P.*
Cryogenic transonic wind tunnels and the condensation of nitrogen*
Expts. in Fluids 11, 333*
1991. `
..30.1:  wall divergence, porosity, suction rate lead to M errors*
SCHEITLE, H.; WAGNER, S.*
Influences of wind tunnel parameters on airfoil characteristics at high subsonic speeds*
Expts. in Fluids 12, 90*
1991. `
..30.1,29.1,59.2: general review from Langley - comments that tunnel design methods are out of date*
GLOSS, B.B.*
Future experimental needs to support applied aerodynamics - a transonic perspective*
AIAA 92-0156*
1992. `
..30.2: holes of all configurations resonate*
MEDVED, B.L.*
An experimental investigation of the static pressure fluctuation mechanism for porous transonic wind tunnel wall configurations*
Expts. in Fluids 15, 401*
1993. `
..30.3: brief description and Baldwin-Lomax calcs*
WILLIAM, K.E.; GESSNER, F.B.; HARLOFF, G.J.*
Design and operation of supersonic annular flow facility*
AIAA J. 32, 1528*
1994. `
..30.0: blowndown to subatmospheric pressure in test section, then 2-stage ejector*
WOLF, S.W.D.; LAUB, J.A.*
Development of the NASA-Ames low-disturbance supersonic wind tunnel for transition studies at Mach 1 . 6*
AIAA 94-0543*
1994. `
..30.3: 90K min. temperature, M<1.3, 2.0x2.4m*
SAUNDERS, T.B.*
The European transonic wind tunnel-testing at flight Reynolds numbers*
AIAA-96-0227*
1996. `