Results 91 to 100 of about 2,285 (153)

Monitoring of Sulfur Mustard (HD) Vapor in the Presence of Absorptive Building Materials. [PDF]

ACS Omega
Oudejans L, See D.
europepmc   +1 more source

Aerodynamic characteristics of a distinct wing-body configuration at Mach 6: Experiment, theory, and the hypersonic isolation principle [PDF]

An experimental investigation has been conducted to determine the effect of wing leading edge sweep and wing translation on the aerodynamic characteristics of a wing body configuration at a free stream Mach number of about 6 and Reynolds number (based on
Penland, J. A., Pittman, J. L.
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Hypersonic aerodynamic characteristics of an all-body research aircraft configuration [PDF]

An experimental investigation was conducted at Mach 6 to determine the hypersonic aerodynamic characteristics of an all-body, delta-planform, hypersonic research aircraft (HYFAC configuration).
Clark, L. E.
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Calibration of transonic and supersonic wind tunnels [PDF]

State-of-the art instrumentation and procedures for calibrating transonic (0.6 less than M less than 1.4) and supersonic (M less than or equal to 3.5) wind tunnels were reviewed and evaluated. Major emphasis was given to transonic tunnels.
Cooksey, J. M., Pope, T. C., Reed, T. D.
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Effect of modifications of aerodynamic characteristics of a single-stage-to-orbit vehicle at Mach 5.9 [PDF]

Hypersonic stability, control, and performance characteristics were determined on a single-stage-to-orbit vehicle based on control-configured stability concepts. The configuration (0.006-scale model) had a large body with a small 50 deg swept wing.
Bernot, P. T.
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The use of actuated flexible plates for adaptive shock control bumps [PDF]

, 2015
Ashill P., Klemens N., Lee D., Rhodes O., Sommerer A., Th., L.   +4 more
core   +1 more source

Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile [PDF]

, 1958
Hanson, P. W., Levey, G. M.
core   +1 more source

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Supersonic Blowdown Wind Tunnel Control Using LabVIEW

46th AIAA Aerospace Sciences Meeting and Exhibit, 2008
A computer-based, proportional-integral control system for supersonic blowdown wind tunnels was developed in a LabVIEW environment. The control algorithm is based on numerically integrating the differential equations used to model a supersonic blowdown wind tunnel in which the proportional and integral control terms were added and tuned in a simulation
Eric Braun, Frank Lu, Philip Panicker, Richard Mitchell, Donald Wilson, J. Dutton   +5 more
openaire   +1 more source

Pressure-Sensitive Paint Measurements in a Blowdown Wind Tunnel

Journal of Aircraft, 2005
A methodology to correct for temperature effects on pressure-sensitive paint data in a blowdown wind tunnel has been suggested. PSP measurements using Optrod-B1 paint were made on an aircraft model instrumented with thermocouples and conventional pressure taps.
Channa Raju, P. R. Viswanath
openaire   +1 more source

Transonic Flow Quality Improvements in a Blowdown Wind Tunnel

Journal of Aircraft, 1973
The development and evaluation of a new type of flow conditioning system between the control valve and stilling chamber of the Vought Systems Division 4 X 4-ft transonic-supersonic wind tunnel are reported. The new system results in a series of normal shocks created by four perforated plates to dissipate total pressure differences between the reservoir
James M. Cooksey, John W. Arnold
openaire   +1 more source