..30.3,49.0:*
DOBLE, W.D.*
Initial investigations into the suppression of flow separation in the 4ft. 6in. by 3ft. 6in. R.M.T.C. wind tunnel.*
ARL, Australia, Aero Note 169*
1958 . `
..30.3,44.2: free piston tunnel*
SCHULTZ, D.L.; JONES, T.V.; OLDFIELD, M.L.G.*
A new transient cascade facility for the measurement of heat transfer rates*
Oxford Univ. Engg Lab. Rept. 1207/77*
1977. `
..30.3:3m x 2m,contraction ratio about 2 to 1 - see Watkins 1984*
HIRD, T.G.*
The design and construction of an industrial wind tunnel*
Royal Melbourne Inst. of Tech. Rept 114001R*
1979. `
..44.2,30.3: final paper on facility - see p.462 for some num calcs*
LAKSHMINARAYANA, B.*
An axial flow research compressor facility designed for flow measurement in rotor passages.*
J. Fluids Engg. 102, 402*
1981. `
..30.3: 86 cm x 20 cm - return cct with centri blower*
BLAIR, M.F.; BAILEY, D.A.; SCHLINKER, R.H.*
Development of a large-scale wind tunnel for the simulation of turbomachinery airfoil boundary layers*
J.Engg. Power 103, 678*
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. `
..30.3: nice hardcover book*
BAALS, D.D.; CORLISS, W.R.*
Wind tunnels of NASA*
NASA SP 440*
1981. `
..04.0,30.3: wall tau from dudy in low-density tunnel - log law goes odd below rtheta=600*
WHITE, B.R.*
Low Reynolds number turbulent boundary layers*
J. Fluids Engg 103, 624*
1981. `
..30.3: 1955 tunnel 1.47<M<4.63*
JACKSON, C.M.; CORLETT, W.A.; MONTA, W.J.*
Description and calibration of the Langley Unitary Plan wind tunnel*
NASA TP1905*
1981. `
..30.3,29.6: 1939 AVA tunnel - improved*
DOBRODZICKI, G.A.*
Flow visualization water tunnel - its construction and capabilities*
NRC Canada Aero Rept LR-610*
1982. `
..30.3:title tanslation amended*
TAKASHIMA, K.*
A survey of three dimensional high Reynolds number wind tunnels*
NASA-TM-76931, N83-23324*
1982. `
..30.3,42.3: 10 level input and output*
STILLINGER, D.C.; HEAD, M.J.; HELLAND, K.N.; VAN ATTA, C.W.*
A closed loop gravity driven water channel for density stratified shear flows*
J. Fluid Mech. 131, 73*
1983. `
..30.3:about time too - diffuser trouble in OJ/CJ VTOL tunnel*
APPLIN, Z.T.*
Flow improvements in the circuit of the Langley 4- by 7-meter tunnel*
NASA TM 85662*
1983. `
..30.3,22.1: Penn State G. Thomas water tunnel*
PARKIN, B.R.*
Hydrodynamics and fluid mechanics*
Naval Research Reviews vol. 35, no. 4, p. 20*
1983. `
..30.3:designed to Mehta, B and P rules - OK, 0.03 percent turb.*
BARRETT, R.V.*
Design and performance of a new low turbulence wind tunnel at Bristol University*
Aero. J. 88, 86*
1984. `
..30.3: same turbulence as in 1941*
McGHEE, R.J.; BEASLEY, W.D.; FOSTER, J.M.*
Recent modifications and calibration of the Langley low-turbulence pressure tunnel*
NASA TP 2328*
1984. `
..30.3:Melbourne - extra screens downstream of fan don't help much. See also Hird 1979*
WATKINS, S.*
Calibration of the industrial wind tunnel*
RMIT WTP 1026*
1984. `
..30.3: 80 cm dia, deformed by 64 jacks*
WEDEMEYER, E.; HEDDERGOTT, A.*
The rubber tube test section of the DFVLR in Gottingen*
DFVLR-FB 85-18*
1985. `
..30.3: 300 pages but incomplete descriptions and few drawings*
PENARANDA, F.E.; FREDA, M.S.*
Aeronautical facilities catalogue. Vol. 1 Wind tunnels*
NASA RP-1132*
1985. `
..32.1,30.3: fibre optics - 200 psi*
SEEGMILLER, H.L.*
Development of a new LDV for the Ames high Reynolds number channel no.II*
Presented at llth ICIASF, Stanford, p. 36*
1985. `
..30.3: improved wide-angle diffuser*
OHMAN, L.H.; BROWN, D.; BOWKER, A.J.; ELLIS, F.A.*
Recent improvements to the NAE 5 ft x ft blowdown wind tunnel*
Canadian NAE-AN-31*
1985. `
..30.3: just so*
BOWDITCH, D.N.*
Current wind tunnel capability and planned improvements at Lewis Research Center*
NASA-TM-87190, N86-18329*
1986. `
..30.3,05.0: water speed 10 to 100 mm/s*
BROWNE, L.W.B.; CHAN, W.K.; ANTONIA, R.A.*
A thick viscous sublayer test facility*
Ninth Australasian Fluid Mech Conf, Auckland New Zealand, p. 524*
1986. `
..30.3:just so*
BRADSHAW, P.*
Wind tunnels and test rigs of the Department of Aeronautics, Imperial College*
Imperial College Aero Rept 86-02, N87-13455*
1986. `
..44.1,30.3: old wind-wave tunnel - new one upcoming*
BOUWMEESTER, R.J.B.; WALLACE, R.G.*
Oil entrainment by breaking waves*
Michigan State Univ., Civ. Engg Dept paper*
1987. `
..24.3,50.0,30.3: prolate spheroid in several tunnels - DNW best*
MEIER, H.U.; MICHEL, U.; KREPLIN, H.P.*
The influence of wind tunnel turbulence on the boundary layer transition*
Perspectives in Turbulence Studies (Rotta Symposium, Gottingen, H.U. Meier and P. Bradshaw, eds.), Springer, p. 26*
1987. `
..30.3,29.6,42.3: just so*
GAD-EL-HAK, M.*
The water towing tank as an experimental facility. An overview*
Expts. in Fluids 5, 289*
1987. `
..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. `
..30.1,30.3: main trouble is the fan support legs (and horrible nacelle shape)*
WADCOCK, A.J.*
The NASA Ames 7 ft. x 10 ft. wind tunnel - present flow quality and recommendations for improvement*
Analytical Methods Report 8705*
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. `
..30.3: review of 13 tunnels*
DRESS, D.A.; KILGORE, R.A.*
Cryogenic wind tunnel research - a global perspective*
Cryogenics vol. 28, no. 1, p. 10*
1988. `
..44.2,30.3: MIT blowdown - AFWAL to have one*
EPSTEIN, A.*
Short duration testing for turbomachinery research and development*
Presented at 2nd Int. Sympo. on Transport, Phenomena, Dynamics, and Design of Rotating Machinery, Honolulu*
1988. `
..30.3: Rolls Royce centrifugal fan and kinky return circuit*
ROACH, P.E.*
A new boundary layer wind tunnel*
Aero. J. 92, 224*
1988. `
..31.1,09.2,30.3: relevant to North Sea oil*
BRUUN, H.H.; FARRAR, B.*
Hot-film probe studies of kerosene/water and gas/liquid flows*
1st World Conf. on Exptl Heat Transfer, Fluid Mech & Thermo. Dubrovnik*
1988. `
..30.3: simply porosint baffles*
LEITH, J.R.; RAETHER, A.M.; SMITH, D.K.*
Wind tunnel facility for operation at very low velocity*
J. Phys. E - Sci. Instrum. 21, 497*
1988. `
..30.3: just so*
SARIC, W.S.; TAKAGI, S.; MOUSSEUX, M.*
The ASU unsteady wind tunnel and fundamental requirements for freestream turbulence measurements*
AIAA-88-0053*
1988. `
..30.3: world's most two-dimensional "tunnel" - continuous running*
GHARIB, M.; DERANGO, P.*
A liquid film (soap film) tunnel to study two-dimensional laminar and turbulent shear flows*
Physica D 37, 406*
1989. `
..42.3,30.3: electrically-heated triangular honeycomb*
LIENHARD V, J.H.; VAN ATTA, C.W.*
Thermally stratifying a wind tunnel for buoyancy influenced flows*
Expts. in Fluids 7, 542*
1989. `
..09.2,30.3: vacuum tunnel and carousel*
LEACH, R.; GREELEY, R.; POLLACK, J.*
Saltation thresholds and entrainment of fine particles at earth and Martian pressures*
NASA TM 102193*
1989. `
..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. `
..42.3,30.3: open circuit wind tunnel -- detailed scaling of results. Pr matters, but Re, lambda less than 50*
LIENHARD V, J.H.; VAN ATTA, C.W.*
The decay of turbulence in thermally stratified flow*
J. Fluid Mech. 210, 57*
1990. `
..30.3: f.s.t. too low to measure*
PATEL, V.C.*
Design and construction of the 1.8m x 1.5m low-turbulence wind tunnel*
IIHR Limited Distribution Report 170, University of Iowa*
1990. `
..30.3: Grenoble - two test sections, including open channel*
BRIANCON-MARJOLLET, L.; MICHEL, J.M.*
The hydrodynamic tunnel of I.M.G. - former and recent equipments*
J. Fluids Engg. 112, 338*
1990. `
..30.3: one wall unit up to 0.8 mm*
BECHERT, D.W.; HOPPE, G.; VAN DER HOEVEN, J.G.T.; MAKRIS, R.*
The Berlin oil channel for drag reduction research*
Expts in Fluids 12, 251*
1992. `
..30.3: Re up to 50 million/ft*
HEDLUND, E.R.; ET AL.*
New high Reynolds number Mach 8 capability*
AIAA J. 30, 1665*
1992. `
..30.3: 0 . 02 percent turbulence. 12 screens, 0 . 62 open area ratio, power factor approx. 0 . 4*
ITO, H.; KOBAYASHI, R.; KOHAMA, Y.*
The low-turbulence wind tunnel at Tohoku University*
Aero J. 96, 141*
1992. `
..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. `
..21.2,30.3: water-driven piston*
PAPANICOLAOU, P.N.*
A piston driven jet for the study of the zone of flow establishment*
Expts. in Fluids 17, 287*
1994. `
..30.3: U. of Waterloo  low-speed suckdown*
KANKAINEN, P.; BRUNDRETT, E.; KAISER, J.A.*
A small wind tunnel significantly improved by a multi-purpose, two-flexible-wall test section*
J. Fluids Engg. 116, 419*
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. `
..30.3: 10 layers with different temperatures*
PICCIRILLO, P.; VAN ATTA, C.W.*
A multiple-source wind tunnel design for producing turbulent shear flows in a stably stratified fluid*
Expts. in Fluids 21, 66*
1996. `
..30.2,30.3: retrospective model tests of Langley VSTOL tunnel. Diffuser stall*
BARNA, P.S.*
Studies of small-scale low-speed wind tunnel configurations*
AIAA 97-0227*
1997. `
..30.2,30.3,49.0: national transonic tunnel (dead). Needed screens in wide-angle diffuser before heat exchanger*
YASTE, D.M.; ET AL.*
NWTC back-leg model tests*
AIAA 97-0093*
1997. `
..30.3,24.4: "substantial regions of quiet flow"*
BLANCHARD, A.E.; LACHOWICZ, J.T.; WILKINSON, S.P.*
NASA Langley Mach 6 quiet wind-tunnel performance*
AIAA J. 35, 23*
1997. `
..42.3,30.3: new 10-layer wind tunnel*
PICCIRILLO, P.; VAN ATTA, C.W.*
The evolution of a uniformly sheared thermally stratified turbulent flow*
J. Fluid Mech. 334, 61*
1997. `
..09.4,30.3: 8 percent for riblets with 30 deg. included angle, height = half pitch (so flat bottom). Berlin oil channel*
BECHERT, D.W.; ET AL.*
Experiments  on drag-reducing surfaces and their optimization with an adjustable geometry*
J. Fluid Mech. 338, 59*
1997. `
..30.3,44.2,17.1: new 1m x 0.2m, 100m/s test rig. Translating-rod wake generator*
SCHOBEIRI, M.T.; PAPPU, K.*
Experimental study on the effect of unsteadiness on boundary layer development on a linear turbine cascade*
Expts. in Fluids 23, 306*
1997. `
..30.3: suckdown, based on 12x12x48in. mailing box and axial vent. fan*
CARLSON, S.*
Caught in a wind tunnel*
Scientific American vol. 277, no. 5, p. 106, November*
1997. `
..05.0,07.0,12.2,30.3: 1.2m x 1.5m x 10m test section. Measured shear correlation coefft. much too low but mean profiles OK (skin friction from Clauser). Re, theta up to 50000*
HITES, M.H.*
Scaling of high-Reynolds number turbulent boundary layers in the National Diagnostic Facility*
PhD thesis, Illinois Inst of Tech.
1997. `
..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. `