12 Matching Results

Search Results

Advanced search parameters have been applied.
in creator/contributor: "Serafini, John S"  
Results: 1 - 12
open access

Impingement of water droplets on wedges and diamond airfoils at supersonic speeds

Description: "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 expressions for the equation of the droplet trajectory, the local rate of impingement and the impingement velocity at any point on the wedge surface, and the total rate of impingement. The analytical expressions are utilized to determine the impingement on the fo… more
Date: July 1953
Creator: Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Impingement of water droplets on wedges and double-wedge airfoils at supersonic speeds

Description: "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 expressions for the equation of the droplet trajectory, the local rate of impingement and the impingement velocity at any point on the wedge surface, and the total rate of impingement. The analytical expressions are utilized to determine the impingement on the fo… more
Date: April 21, 1953
Creator: Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow

Description: 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-stream static temperatures to -.40^o F."
Date: January 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Graphical Method for Obtaining Flow Field in Two-Dimensional Supersonic Stream to Which Heat Is Added

Description: 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 the direction of the flow.
Date: November 1950
Creator: Pinkel, I. Irving & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow

Description: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
Date: January 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method for Rapid Determination of the Icing Limit of a Body in Terms of the Stream Conditions

Description: "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-Mach number, altitude, and stream temperature which will maintain an ice-free surface in an icing cloud. The method can be applied to both subsonic and supersonic flow. The charts presented are for Mach numbers up to 1.8 and pressure altitudes from sea level to 4… more
Date: March 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A preliminary investigation of static-pressure changes associated with combustion of aluminum borohydride in a supersonic wind tunnel

Description: 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 portion of the test section. Results regarding the static-pressure increases, effect of change in fuel-injection rate, and effect of tunnel boundary layer on the character of the heat-addition region are provided.
Date: August 18, 1955
Creator: Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Impingement of water droplets on an NACA 65(sub 1) -212 airfoil at an angle of attack of 4 degrees

Description: The trajectories of droplets in the air flowing past an NACA 651-212 airfoil at an angle of attack of 40 were determined. The collection efficiency, the area of droplet impingement, and the rate of droplet impingement were calculated from the trajectories and are presented herein.
Date: September 10, 1952
Creator: Brun, Rinaldo J.; Serafini, John S. & Moshos, George J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Impingement of Cloud Droplets on Aerodynamic Bodies as Affected by Compressibility of Air Flow Around the Body

Description: 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 compared with calculations of trajectories in an incompressible flow field. Results regarding the extension of cylinder results to airfoils are provided.
Date: March 1953
Creator: Brun, Rinaldo J.; Serafini, John S. & Gallagher, Helen M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distribution and Aerodynamic Coefficients Associated With Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing

Description: "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 symmetrical circular-arc wing are presented in this report. The pressure distributions are obtained by the use of graphical method which gives the two-dimensional supersonic inviscid flow field obtained with moderate heat addition. The variation is given of the lift-dra… more
Date: February 14, 1952
Creator: Pinkel, I. Irving; Serafini, John S. & Gregg, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory investigation of aerodynamic effects of external combustion of aluminum borohydride in airstream adjacent to flat plate in Mach 2.46 tunnel

Description: 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 schileren motion pictures of the flame and associated shock waves were taken. Results regarding the description of the combustion and associated stream disturbances, static-pressure change at model reference surface caused by combustion, lift forces resulting from co… more
Date: July 29, 1957
Creator: Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory investigation of static- and base-pressure increases resulting from combustion of aluminum borohydride adjacent to body of revolution in supersonic wing tunnel

Description: Report presenting pressure distribution associated with the stable combustion of aluminum borohydride about a body of revolution in a wind tunnel at Mach number 2.47. Pressure increases on the cylindrical and base surfaces of the model were measured. Results regarding the burning and associated flow phenomena, axial and meridional static-pressure data obtained during combustion, and base-pressure data during combustion are provided.
Date: October 2, 1957
Creator: Serafini, John S.; Dorsch, Robert G. & Fletcher, Edward A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen