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Preliminary investigation of porous walls as a means of reducing tunnel boundary effects at low-supersonic Mach numbers

Description: Report presenting the use of porous-walled tunnels at supersonic Mach numbers as a means of avoiding reflection of a stream disturbance extending to the walls. Results from analysis and an experiment with a 4 degree wedge at a Mach number of 1.2 are provided.
Date: September 13, 1950
Creator: Nelson, William J. & Bloetscher, Frederick
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of the zero-lift pressure distribution over a wedge airfoil in closed, slotted, and open-throat tunnels at transonic Mach numbers

Description: Report presenting pressure distributions and Schileren photographs of the flow around a 10-percent-thick diamond airfoil at zero lift in two-dimensional closed, slotted, and open-throat tunnels. Results regarding the effect of slot area ratio and effect of slot spacing are provided.
Date: June 16, 1952
Creator: Nelson, William J. & Bloetscher, Frederick
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Multiple Jet-Exit Installations

Description: Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Transonic Investigation of the Aerodynamic Characteristics of Plate- and Bell- Type Outlets for Auxiliary Air

Description: Report presenting an investigation of the aerodynamic characteristics of several plate- and bell-type outlets discharging air into a transonic stream. The variation in discharge coefficient of the outlets is presented as a function of the rate of discharge. The discharge coefficient, jet wake, and surface pressure distribution are also provided.
Date: September 3, 1952
Creator: Nelson, William J. & Dewey, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of constant-geometry, variable Mach number, supersonic tunnel with porous walls

Description: Report presenting a method of generating variable Mach number supersonic flow in a channel of fixed geometry by the removal of air through uniform porous walls. Calculated porosity distributions are presented for several minimum-length nozzles designed to operate at Mach numbers up to 2.0. Experimental and analytical data is presented.
Date: May 3, 1950
Creator: Nelson, William J. & Klevatt, Paul L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Effects of Inlet Asymmetry on the Performance of Converging-Diverging Diffusers at Transonic Speeds

Description: Report presenting the effects of inclining the plane of the inlet on the performance of several converging-diverging diffusers at zero angle of attack for a range of Mach numbers. Results regarding Schileren photographs, static-pressure recovery, total-pressure loss, and total-pressure distributions are provided.
Date: November 25, 1952
Creator: Dennard, John S. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Slotted-boundary interference effects on wedge airfoils at low supersonic Mach numbers

Description: Report presenting an experimental investigation of pressure disturbances caused by the reflection of two-dimensional shock waves from a slotted boundary at Mach numbers between 1.0 and 1.5. Simple-wedge airfoils with three different apex angles were used to generate shock waves and the static pressures ere measured at various points along the surface of each airfoil.
Date: July 30, 1953
Creator: Nelson, William J. & Vick, Allen R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of multiple jet-exit installations

Description: Report presenting an investigation of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. The data were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results indicated that large base-pressure drag coefficients may be encountered in the transonic and low supersonic speed range and that the best configuration in the test was boattailed between the nacelles, had a cylindrical nacelle afterbody, and a divergent nozzle with a design pressure … more
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet effects on the base drag of a cylindrical afterbody with extended nozzles

Description: A wind-tunnel investigation to determine the effects of both single and twin jets on base drag of a cylindrical body has been conducted at Mach numbers from 0.6 to 1.4. The plane of the jet exit was varied with respect to that of the afterbody. Jet total-pressure ratio ranged up to 20. Significant improvements in base drag were obtained by extending the plane of the jet exits beyond the afterbody base and by venting the base cavity to the external stream.
Date: April 15, 1958
Creator: Nelson, William J. & Scott, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Air Flow Around a Martin PBM-3 Flying Boat by Means of Tufts

Description: Report presenting observations made of the air flow around a Martin PBM-3 flying boat. The observations are part of an analysis to aid in the determination of possible methods of reducing the air drag of the airplane. The behavior of the tufts on the hull and tip floats at various airplane speeds by still and moving pictures taken from an accompanying airplane.
Date: April 1943
Creator: Nelson, William J. & Ebert, John W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of slot location and geometry on the flow in a square tunnel at transonic Mach numbers

Description: Report presenting data from an investigation of the effects of slot location and slot geometry on the flow in a square tunnel for a Mach number range up to 1.4. Calculated static-pressure and angle-of-flow distributions along the slotted boundary are presented for several slot configurations in a tunnel with two opposite walls slotted.
Date: November 25, 1953
Creator: Nelson, William J. & Cubbage, James M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4

Description: Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.
Date: April 7, 1953
Creator: Nelson, William J. & Cubbage, James M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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