5 Matching Results

Search Results

Advanced search parameters have been applied.
in creator/contributor: "Cohen, Nathaniel B"  
Results: 1 - 5
open access

A Power-Series Solution for the Unsteady Laminar Boundary-Layer Flow in an Expansion Wave of Finite Width Moving Through a Gas Initially at Rest

Description: Note presenting a consideration of the equations of motion and energy for the laminar boundary layer flow in an expansion wave of finite width moving into undisturbed fluid, such as in a shock tube. Solutions in the form of infinite power series for velocity and local enthalpy functions were indicated and the first three terms of each series were numerically evaluated. Results regarding numerical information, a discussion of the results, a comparison with the solution of the zero-thickness expa… more
Date: June 1957
Creator: Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theory for predicting the flow of real gases in shock tubes with experimental verification

Description: Report presenting the nonlinear characteristic differential equations applicable to a quasi-one-dimensional unsteady channel flow with friction and heat transfer, which are linearized and integrated in functional form for the particular study of small perturbations from ideal shock-tube flows.
Date: March 1955
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison

Description: Report presenting a modification of the linearized attenuation theory by using an unsteady compressible local skin-friction coefficient, a nonlinear approach, and the consideration of transition effects. Curves for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers are provided.
Date: September 1958
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An integral solution to the flat-plate laminar boundary-layer flow existing inside and after expansion waves and after shock waves moving into quiescent fluid with particular application to the complete shock-tube flow

Description: Report presenting a solution to the unsteady two-dimensional laminar boundary-layer flow inside centered expansion waves and behind both centered expansion waves and shock waves using an extension of the Karman-Pohlhausen method. The Prandtl unsteady-boundary-layer equations are also integrated normal to the surface bounding the flow and are transformed into a conical coordinate system. The solution to the two-dimensional unsteady laminar boundary layer existing at all points in an air-air shoc… more
Date: June 1957
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Several Modifications to Center Body and Cowling on Supercritical Performance of a Supersonic Inlet at Mach Number of 2.02

Description: Report discussing an investigation of several modifications of the center body and cowling of a supersonic inlet at Mach number 2.02 and angles of attack up to 12.25 degrees. Information about the effect on stable range of boundary-layer control on the center body, the stable range of distortion of conical shock, and the stable range of cowling-lip thickness is provided.
Date: May 20, 1955
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen