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in subjects: "wind tunnels"

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[News Clip: David Wind Tunnel]

Video footage from the KXAS-TV/NBC station in Fort Worth, Texas, to accompany a news story.

Date: September 16, 2003

Duration: 2 minutes 55 seconds

Creator: NBC 5 (Television station : Fort Worth, Tex.)

Item Type: Video

Partner: UNT Libraries Special Collections

open access

The Electrodynamometric Balance of the Small Wind Tunnel of the French Service of Aeronautical Research

This investigation shows the attempt to improve the electrodynamomoter designed by Mr. Villey. The force to be measured acts on a flexible steel plate which is placed in front of a fixed plate. The deformation varies the original thickness of the layer of air between the two plates, thus causing a more rapid variation in the coefficient of electrostatic attraction of the two plates than in the capacity of the condenser formed by the dynamometer.

Date: March 1930

Creator: Rebuffet, P.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Acoustical Treatment for the NACA 8- by 6-Foot Supersonic Propulsion Wind Tunnel

"This report presents results of a research and engineering program performed during the first half of 1950 that resulted in an acoustical treatment for the 8- by 6-foot supersonic wind tunnel at the Lewis Flight Propulsion Laboratory" (p. 1).

Date: June 1955

Creator: Beranek, Leo L.; Labate, Samuel & Ingard, Uno

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The aerodynamics of a wind-tunnel fan

From Introduction: "This paper deals only with the aerodynamics of the fan proper and demonstrates the manner in which the radial distribution of axial velocity of fluid through a fan is governed by geometry of the fan itself."

Date: August 1941

Creator: Corson, Blake W.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Ames 10- by 14-Inch Supersonic Wind Tunnel

"The purpose of the present report is to describe the 10- by 14-inch supersonic wind tunnel and its operational characteristics over the nominal Mach number range from 2.7 to 6.3. Rather complete calibration data on characteristics of flow in the test section are presented and briefly discussed" (p. 2).

Date: January 1954

Creator: Eggers, A. J., Jr. & Nothwang, George J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Analysis and comparison with theory of flow-field measurements near a lifting rotor in the Langley full-scale tunnel

From Introduction: "The time-averaged flows are considerably simpler to deal with theoretically than are the instantaneous flows, and the results of several theoretical analyses are available (refs. 2 to 6, for example). Several previous experimental investigations (see ref. 7 for a bibliography) have provided some qualitative information on the subject by the use of smoke in flight and in wind tunnels. However, quantitative measurements (refs. 8 to 10) are extremely scarce and, in general, are… more

Date: April 1956

Creator: Heyson, Harry H.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Analysis of an induction blowdown supersonic tunnel

From Introduction: "In the present paper, general ejector equations (see reference 4 or 5) and certain assumptions with regard to flow conditions and pressure losses have been utilized to calculate the running times of induction blowdown supersonic tunnels operating in the mentioned Mach number range."

Date: April 1950

Creator: Bidwell, Jerold M.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Aerodynamic Characteristics of a Model Wing Having a Split Flap Deflected Downward and Moved to the Rear

"Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their … more

Date: May 1932

Creator: Weick, Fred E. & Harris, Thomas A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Aerodynamic Forces and Moments on a Spinning Model of the F4B-2 Airplane as Measured by the Spinning Balance

"The tests described in this report were made as part of an investigation of the spinning characteristics of the F4B-2 airplane conducted at the request of the Bureau of Aeronautics, Navy Department" (p. 1).

Date: February 1935

Creator: Bamber, M. J. & Zimmerman, C. H.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Italian and French Experiments on Wind Tunnels

Given here are the results of experiments conducted by Colonel Costanzi of the Italian Army to determine the influence of the surrounding building in which a wind tunnel was installed on the efficiency of the installation, and how the efficiency of the installation was affected by the design of the tunnel. Also given are the results of a series of experiments by Eiffel on 34 models of tunnels of different dimensions. This series of experiments was started in order to find out if, by changing th… more

Date: November 1920

Creator: Knight, William

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the convention… more

Date: November 6, 1947

Creator: Eggers, A. J., Jr.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

From Introduction: "This report presents an analysis based on flight and wind-tunnel test data directed toward the determination of the probable cause of the pitch-up. Wing pressure distribution and stability and control characteristics in the dive are also included."

Date: September 25, 1947

Creator: Brown, Harvey H.; Rolls, L. Stewart & Clousing, Lawrence A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation of a large-scale model at low speed

From Introduction: "This report presents the aerodynamic characteristics at low speed end high Reynolds number as determined in the Ames 40- by 80 foot wind tunnel."

Date: January 21, 1949

Creator: McCormack, Gerald M. & Walling, Walter C.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 1: maximum thickness at 20 percent of the chord

From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."

Date: November 19, 1948

Creator: Berggren, Robert E. & Summers, James L.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics for Symmetrical Wing Sections at High Subsonic and Moderate Supersonic Mach Numbers

From Summary: "Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63^o and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51."

Date: July 7, 1949

Creator: Mas, Newton A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection

From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."

Date: June 15, 1948

Creator: Dietz, Robert O., Jr.; Wishnek, George & Kuenzig, John K.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbe… more

Date: June 30, 1949

Creator: Bandettini, Angelo & Reed, Verlin D.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

From Introduction: "The Ames Aeronautical Laboratory has in progress an experimental investigation of the aerodynamic characteristics of wings of interest in the design of high-speed fighter aircraft. This program included an investigation in the Ames 6-by 6-foot supersonic wind tunnel at both subsonic and supersonic Mach numbers of a wing-body combination having a 3-percent-thick, unswept, tapered wing with circular-arc sections and an aspect ratio of 3.1 (reference 1).

Date: May 2, 1952

Creator: Emerson, Horace F. & Gale, Bernard M.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."

Date: February 6, 1951

Creator: Sutton, Fred B. & Martin, Andrew

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The Ames supersonic free-flight wind tunnel

From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."

Date: April 25, 1952

Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Altitude Wind Tunnel Investigation of High-Temperature Afterburners

From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques pre… more

Date: June 26, 1952

Creator: Conrad, E. William & Campbell, Carl E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Altitude investigation of XJ34-WE-32 engine performance without electronic control

From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."

Date: May 29, 1953

Creator: Bloomer, Harry E.; Walker, William J. & Pantages, George L.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Analysis of Wind-Tunnel Data on Directional Stability and Control

From Summary: "This paper does not attempt to establish criterions for directional stability and control; rather, the emphasis is placed on providing some basis for design to specified criterions. An example applying the design methods has been included."

Date: September 1940

Creator: Pass, H. R.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.

Date: July 21, 1942

Creator: Becker, John V. & Baals, Donald D.

Item Type: Report

Partner: UNT Libraries Government Documents Department