Hypersonic aerodynamic characteristics of a variable-dihedral delta-wing spacecraft configuration
Wind tunnel stability tests of variable dihedral delta wing spacecraft configuration at hypersonic speed
Ellison, J. C.↗
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Dynamic support interference - Fact or fiction
Aerodynamic support interference in wind tunnel testing of configurations involving bulbous base, mass addition, transition near base and hypersonic low density flows
Ericsson, L. E.↗
Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated
A study has been made to determine the aerodynamic characteristics of a low-aspect ratio cruciform missile model with all-movable wings and tails. The configuration was tested at Mach numbers from 1.50 to 4.63 with the wings in the vertical and horizontal planes and with the wings in a 45 deg roll plane with tails in line and interdigitated.
Graves, E. B.↗
Experimental investigation of hypersonic buzz on a high cross-range shuttle configuration
A wind tunnel investigation has been conducted to determine the nature of an unsteady hypersonic flow phenomenon, often referred to as hypersonic buzz, on a 1:100 scale model representative of a high cross-range shuttle configuration. The tests, conducted in helium at a nominal Mach number of 17.5, were specifically directed at obtaining a better understanding of the character of the hypersonic flow field in the vicinity of a deflected control surface. Power spectral densities and root mean squared values of surface pressure fluctuations are presented along with observations made from high speed motion pictures, schlieren and oil flow photographs. Flap deflections of 0, 20, 30, 35, 40 and 60 deg were tested at various angles of attack from 0 deg to 37 deg. It is quite clear from these tests that, under certain conditions, extremely unstable hypersonic flow patterns are formed.
Goldman, R. L.↗
Autorotating wings - An experimental investigation.
The autorotation of a flat plate about its spanwise axis was experimentally studied. Most of the work was done with a wing mounted in a 5 x 7 ft low-speed wind tunnel. The measurements consisted of the unsteady lift, drag, angular acceleration and the wing rotation rate. The flow pattern was very different from that over a static wing. The maximum and average lift, drag and angular acceleration were measured for Reynolds numbers from 25,000 to 250,000. The effect of applying driving and retarding torques to the wing was studied. A variety of wing configurations were tested, together with freely falling wings. For Reynolds numbers above 4000 the average lift and drag coefficients were comparable to those observed in the fixed axis tests, and it appeared that the flow pattern was similar.
Smith, E. H.↗
Correcting for nonlinear effects in fracture toughness testing.
Expressions for fracture toughness, which include nonlinear effects due to crack front plastic yield and possible small crack extension prior to fracture instability, are obtained for several test specimen configurations. Inclusion of such effects is based on a simple compliance type determination of the total energy rate at onset of fast fracture.
Liebowitz, H.↗
Flap noise
Externally-blown-flap noise research can be summarized by the following remarks: With lower-surface blowing, the sources of the flap noise are begining to be understood and the noise scaling laws have been established. Further, progress has been made on suppressing the flap interaction noise at the large flap deflections used during landing. Recent small-scale noise tests of configurations using external upper-surface blowing indicate that engine-over-the-wing configurations may be promising.
Dorsch, R. G.↗
Longitudinal aerodynamic and propulsion characteristics of a propulsive-wing V/STOL model at high subsonic speeds
The aerodynamic and propulsion characteristics of a 1/6-scale propulsive-wing V/STOL air-powered model was investigated over the Mach number range from 0.40 to 0.96 and at angles of attack from -5 deg to 15 deg for several fan rotational speeds. Three fanduct-exit configurations were tested, including two exit areas. The model with 25-percent-thick wing had a drag-rise Mach number of 0.85, which is typical of aircraft with thinner, conventional, unswept wings.
Salters, L. B., Jr.↗
Low-frequency rear quadrant noise of a turbojet engine with exhaust duct muffling
A J-65 engine was run with a tuned sound-absorbing exhaust duct to study the internal and jet components of rear quadrant noise. Full muffler, hard wall duct, and regular production engine configurations were tested. The jet exhaust velocities were subsonic. The use of the exhaust muffler extended the relation between the jet noise and the eighth power of the jet velocity to lower velocities than for the hard wall duct.
Woodward, R. P.↗
Aerodynamic effects of five lift-fan pod arrangements on an unpowered V/STOL transport model
An investigation was conducted in the Langley V/STOL tunnel to determine the effect of longitudinally oriented wing-mounted pods on the longitudinal and lateral aerodynamic characteristics in the cruise flight condition of a high-wing V/STOL transport model. Five pod arrangements were tested - three configurations with in-line pods at 20, 40, or 60 percent semispan and two split pod configurations with rear pods at 20 percent semispan and front pods at 40 or 60 percent semispan. In general, addition of the pods to the model decreased the stability, increased the lift-curve slope, and alleviated the abrupt stall of the basic model. The configuration with pods at 20 percent semispan had an abrupt instability at 10 deg angle of attack, All the configurations had lateral stability at sideslip angles from 5 to -5 deg. Very little difference in results existed between the configurations with pods at 40 and 60 percent semispan. Of the split pod configurations, the configuration with front pods at 40 percent semispan offered the best trimmed lift and lift-induced drag characteristics at high angles of attack. The configuration with in-line pods at 40 or 60 percent semispan provided the best cruise characteristics of all the pod configurations.
Thomas, J. L.↗
Stability and control characteristics of a Langley concept space shuttle orbiter (LO-100) at low subsonic speeds
An experimental aerodynamic investigation was conducted on a 0.01 scale model of a Langley concept space shuttle orbiter (LO-100) in the Langley Low Turbulence Pressure Tunnel at a Mach number of 0.25 and at a Reynolds number of 5.4 million per foot. The angle of attack was varied from about -2 deg to 24 deg at 0 deg and 5 deg sideslip. The configuration was tested at elevon settings of 0 deg, -5 deg, -10 deg, and -15 deg for a body base flap setting of 0 deg and at 0 deg, -10 deg, and -15 deg for a body base flap setting of -18 deg. The effect of rudder flare angle was obtained using 0 deg, 20 deg, and 40 deg, flare settings.
Spencer, B., Jr.↗
Thermal protection system gap heating rates of the Rockwell International flat plate heat transfer model (OH2A/OH2B)
Heat transfer data for the Rockwell International Flat Plate Thermocouple Model are presented. The model simulated the Space Shuttle Vehicle Thermal Protection System. Data were recorded for locations in and around various size gaps for various gap orientation configurations. The test was conducted at Mach 5.1 for free-stream Reynolds number per foot values from 500,000 to 1,500,000.
Foster, T. F.↗
Distributed educated throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction
The results of an experimental investigation to increase the stable airflow operating range of a supersonic mixed-compression inlet are presented. A distributed educated throat stability-bypass entrance configuration was tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 16.1 percent was obtained if a constant pressure was maintained in the bypass plenum. Limited unstart angle of attack data are presented.
Shaw, R. J.↗
Comparison of cooling effectiveness of turbine vanes with and without film cooling
The cooling effectiveness of three film-cooled vanes were compared to the cooling effectiveness of two non-film-cooled vanes. The comparison indicated that, for the vane configurations and test conditions examined, film cooling had an adverse effect near the suction-surface trailing edge of the vanes. Film cooling was found to be beneficial on the pressure surface of the vanes.
Yeh, F. C.↗
Effect of canard location and size on canard-wing interference and aerodynamic center shift related to maneuvering aircraft at transonic speeds
A generalized wind-tunnel model, typical of highly maneuverable aircraft, was tested in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.70 to 1.20 to determine the effects of canard location and size on canard-wing interference effects and aerodynamic center shift at transonic speeds. The canards had exposed areas of 16.0 and 28.0 percent of the wing reference area and were located in the chord plane of the wing or in a position 18.5 percent of the wing mean geometric chord above or below the wing chord plane. Two different wing planforms were tested, one with leading-edge sweep of 60 deg and the other 44 deg; both wings had the same reference area and span. The results indicated that the largest benefits in lift and drag were obtained with the canard above the wing chord plane for both wings tested. The low canard configuration for the 60 deg swept wing proved to be more stable and produced a more linear pitching-moment curve than the high and coplanar canard configurations for the subsonic test Mach numbers.
Gloss, B. B.↗
Acoustic liner performance in the presence of a mean flow and three-dimensional wave motion
Experiments were performed to check the applicability of existing acoustic liner design procedures. The performance of three different liner configurations was tested in a duct containing three-dimensional wave motion and a one-dimensional mean flow past the liner surface. Both the local liner admittance and the overall wave attenuation provided by various liner-nozzle combinations were measured with sonic flow at the nozzle throat. The experimental data are compared with predictions from current theoretical analyses, and the comparison is used to evaluate the theories.
Bell, W. A.↗
Measurements of the vortex wakes of a subsonic and supersonic transport model in the 40 by 80 foot wind tunnel
The rolling moment induced on aircraft models in the wake of a model of a subsonic transport and of a supersonic transport was measured as a function of angle of attack for several configurations. The tests are described and an analysis of the data is given in this memorandum.
Rossow, V. J.↗
Laser tuners using circular piezoelectric benders
The paper presents the results of an experimental evaluation of a new type of piezoelectric ceramic device designed for use as a laser mirror tuner. Thin plates made from various materials were assembled into a circular bimorph configuration and tested for linearity of movement, maximum travel, and resonant frequency for varying conditions of clamping torque and mirror loading values. Most of the devices tested could accept mirror diameters up to approximately 1.3 cm and maintain a resonant frequency above 2 kHz. Typical mirror translation without measurable tilt was plus or minus 20 micrometers or greater for applied voltages of less than plus or minus 300 V.
Mcelroy, J. H.↗