John S Serafini
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An analytical and experimental investigation of resistojet plumes Open
As a part of the electrothermal propulsion plume research program at the NASA Lewis Research Center, efforts have been initiated to analytically and experimentally investigate the plumes of resistojet thrusters. The method of G.A. Simons f…
An analytical and experimental comparison of the flow field of an advanced swept turboprop Open
An argon ion laser velocimeter with four beams was used to measure the detailed flow-field of an advanced eight blade propeller with 45% of tip sweep in an 8x6 foot supersonic wind tunnel. Data were obtained at a free stream Mach number of…
Preliminary measurements of plasma fluctuations in an 8-cm mercury ion thruster Open
The rms magnitude, spectra, and cross correlations for the fluctuations in the beam current, the neutralizer keeper current, and the discharge current and voltage were measured for an 8-cm diameter, dished grid ion thruster for a beam curr…
Correlation measurements of plasma fluctuations in a Hall current accelerator. Open
Correlation measurements on plasma oscillations in Hall accelerator with axial electric field, radial magnetic field, and argon discharge
On the utility of conventional turbulence experimental methods in the study of plasma fluctuations Open
Fluid dynamics turbulence experimental methods applications in study of plasma fluctuations, particularly space-time correlation and spectral techniques
Exploratory Investigation of Aerodynamic Effects of External Combustion of Aluminum Borohydride in Airstream Adjacent to Flat Plate in Mach 2.46 Tunnel Open
Report presenting pressure distributions associated with stable combustion of aluminum borohydride in the supersonic stream adjacent to a short, 13-inch chord, and an extended, 25-inch chord, flat-plate model. High-speed direct and schiler…
A Preliminary Investigation of Static-pressure Changes Associated with Combustion of Aluminum Borohydride in a Supersonic Wind Tunnel Open
Report presenting static-pressure changes resulting from steady combustion of aluminum borohydride in a supersonic wind tunnel. Static pressures were measured along the top wall of a tunnel adjacent to the flame that filled the upper porti…
Impingement of Cloud Droplets on a Cylinder and Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method Open
"Evaluation of the rotating multicylinder method for the measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds showed that small uncertainties in the basic data eliminate the distinction b…
Impingement of water droplets on wedges and double-wedge airfoils at supersonic speeds Open
An analytical solution has been obtained for the equations of motion of water droplets impinging on a wedge in a two-dimensional supersonic flow field with a shock wave attached to the wedge. The closed-form solution yields analytical expr…
Impingement of water droplets on wedges and diamond airfoils at supersonic speeds Open
An analytical solution has been obtained for the equations of motion of water droplets impinging on a wedge in a two-dimensional supersonic flow field with a shock wave attached to the wedge. The closed-form solution yields analytical expr…
Impingement of cloud droplets on aerodynamic bodies as affected by compressibility of air flow around the body Open
Note presenting the computation of the trajectories of water droplets in a compressible-air flow field around a cylinder using a mechanical analog. The results of the calculations at approximately the flight critical Mach number were compa…
A Method for Rapid Determination of the Icing Limit of a Body in Terms of the Stream Conditions Open
"The effects of existing frictional heating were analyzed to determine the conditions under which ice formations on aircraft surfaces can be prevented. A method is presented for rapidly determining by means of charts the combination of-Mac…
Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow Open
From Introduction: "The results presented herein were calculated for a symmetrical diamond airfoil at zero angle of attack for a range of airfoil-thickness ratios from 0.02 to 0.10, pressure altitude from sea level to 45,000 feet, and free…
Pressure distribution and aerodynamic coefficients associated with heat addition to supersonic air stream adjacent to two-dimensional supersonic wing Open
"The modifications in the pressure distributions and the aerodynamic coefficients associated with additions of heat to the two-dimensional supersonic in viscid flow field adjacent to the lower surface of of a 5-percent-thickness symmetrica…
Graphical Method for Obtaining Flow Field in Two-Dimensional Supersonic Stream to Which Heat Is Added Open
Report presenting a graphical method for obtaining the two-dimensional supersonic flow with moderate heat addition. The basic equations were derived for flows in which the total temperature has a continuous variation with displacement in t…