The Cryogenic Wind Tunnel for High Reynolds Number Testing

Abstract

Both capital and operating costs appear acceptable.

Cryogenic transonic wind tunnels and the condensation of nitrogen

“…But this counts power for the tunnel drive only while the power to produce the cold gas is not included. Overall for a range of 88< T<ll0 K, and 1 <po<5 atm, we find (Kilgore, 1974) 4.4 < (Recrro)/(Reco,) < 5.8,…”

“…1, however, the vapor pressure curve is given only above the melting point. The Chinese experiments are shown together with four isentropes typical for the Langley facility (Kilgore, 1974) in a temperature range of 90< To < 105 K at po=2.5 atm. Pressure Pl, is the test section static pressure at M = 0.8.…”

Selected Scientific and Technical Contributions of Edward C. Polhamus

“…A portion of the Branch research team involved in creating the 0.3-m TCT is shown in Figure 31, and many other people had become involved by this time. Polhamus had engendered a very effective team, and among the key contributions was the conceptual work from Kilgore 33 , developmental work from Goodyer and Kilgore 34 , real gas effects from Adcock 35 , and condensation work from Hall 36 .…”

Hydrogen tube vehicle for supersonic transport: 3. Atmospheric merit

“…High Mach-number wind tunnels use helium as the test gas to prevent liquefaction in the nozzle during expansion [12]. Heavy test gases such as Freon increase the Reynolds number because of their density [13], and cryogenic wind tunnels using nitrogen increase the Reynolds number because low temperature increases density and decreases viscosity [14].…”