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 Collection: Technical Report Archive and Image Library
NACA Mach number indicator for use in high-speed tunnels

NACA Mach number indicator for use in high-speed tunnels

Date: July 1, 1943
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Numerical evaluation of mass-flow coefficient and associated parameters from wake-survey equations

Numerical evaluation of mass-flow coefficient and associated parameters from wake-survey equations

Date: August 1, 1947
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations VI : swept-wing heavy-bomber configuration with stores of different sizes and shapes

The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations VI : swept-wing heavy-bomber configuration with stores of different sizes and shapes

Date: March 8, 1956
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of static forces on internally carried bombs of three fineness ratios in flow field of a swept-wing fighter-bomber configuration at a Mach number of 1.61 with illustrative drop-path calculations

Measurement of static forces on internally carried bombs of three fineness ratios in flow field of a swept-wing fighter-bomber configuration at a Mach number of 1.61 with illustrative drop-path calculations

Date: January 10, 1957
Creator: Smith, Norman F & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations III : swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61

The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations III : swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61

Date: September 15, 1955
Creator: Smith, Norman F & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of configuration variables on store loads at supersonic speeds

Some effects of configuration variables on store loads at supersonic speeds

Date: July 6, 1955
Creator: Smith, Norman F & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration

An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration

Date: February 1, 1956
Creator: Smith, Norman F & Hasel, Lowell E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : force characteristics of the complete configuration and its various components at Mach numbers of 1.40 and 1.59

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : force characteristics of the complete configuration and its various components at Mach numbers of 1.40 and 1.59

Date: January 22, 1951
Creator: Smith, Norman F & Marte, Jack E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712

As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712

Date: October 17, 1952
Creator: Smith, Norman F. & Hasel, Lowell E.
Description: An investigation of the aerodynamic characteristics of an 0.025-scale model of the MX-1712 configuration has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel. The tests were performed at Mach numbers of 1.41 and 2.01 at a Reynolds number of approximately 2.6 x 10(exp 6) based on the wing mean aerodynamic chord The MX-1712 is a proposed swept-wing, jet-powered supersonic bomber aircraft. The wing is of aspect ratio 3.5, taper ratio 0.2, and thickness ratio 5.5 percent (streamwise) and has 47deg sweep of the quarter-chord line. The longitudinal and lateral force characteristics of the model and various combinations of its components, including several nacelle installations, were investigated. The effects of a modified wing, two horizontal tail positions, and a shortened fuselage were also studied. The results obtained from these investigations are presented in this report. The aerodynamic investigation of this model disclosed no unusual stability characteristics or Mach number effects. The choice of nacelle installations appears to be a major decision, one greatly affecting the performance of the airplane, At M = 1.41 and C(sub L) = 0.1, the buried nacelles increased the drag of the basic model by 9 percent, while the best pod nacelles increased the ...
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback : a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback : a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Date: April 20, 1951
Creator: Smith, Norman F; Kainer, Julian H & Webster, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic theory and test of strut forms. Part I

Aerodynamic theory and test of strut forms. Part I

Date: May 1928
Creator: Smith, R H
Description: This report presents the first part of a two part study made under this title. In this part the symmetrical inviscid flow about an empirical strut of high service merit is found by both the Rankine and the Joukowsky methods. The results can be made to agree as closely as wished. Theoretical stream surfaces as well as surfaces of constant speed and pressure in the fluid about the strut are found. The surface pressure computed from the two theories agrees well with the measured pressure on the fore part of the model but not so well on the after part. From the theoretical flow speed the surface friction is computed by an empirical formula. The drag integrated from the friction and measured pressure closely equals the whole measured drag. As the pressure drag and the whole drag are accurately determined, the friction formula also appears trustworthy for such fair shapes. (author).
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic theory and tests of strut forms. Part II

Aerodynamic theory and tests of strut forms. Part II

Date: May 1929
Creator: Smith, R H
Description: This report presents the second of two studies under the same title. In this part five theoretical struts are developed from distributed sources and sinks and constructed for pressure and resistance tests in a wind tunnel. The surface pressures for symmetrical inviscid flow are computed for each strut from theory and compared with those found by experiment. The theoretical and experimental pressures are found to agree quantitatively near the bow, only qualitatively over the suction range, the experimental suctions being uniformly a little low, and not at all near the stern. This study is the strut sequel to Fuhrmann's research on airship forms, the one being a study in two dimensions, the other in three. A comparison of results indicates that the agreement between theory and experiment is somewhat better for bodies of revolution than for cylinders when both are shaped for slight resistance. The consistent deficiency of the experimental suctions which is found in the case of struts was not found in the case of airships, for which the experimental suctions were sometimes above sometimes below their theoretical values.
Contributing Partner: UNT Libraries Government Documents Department
Air force and moment for N-20 wing with certain cut-outs

Air force and moment for N-20 wing with certain cut-outs

Date: November 29, 1926
Creator: Smith, R H
Description: The airplane designer often finds it necessary, in meeting the requirements of visibility, to remove area or to otherwise locally distort the plan or section of an airplane wing. This report, prepared for the Bureau of Aeronautics January 15, 1925, contains the experimental results of tests on six 5 by 30 inch N-20 wing models, cut out or distorted in different ways, which were conducted in the 8 by 8 foot wind tunnel of the Navy Aerodynamical Laboratory in Washington in 1924. The measured and derived results are given without correction for vl/v for wall effect and for standard air density, p=0.00237 slug per cubic foot.
Contributing Partner: UNT Libraries Government Documents Department
Lift, drag, and elevator hinge moments of Handley Page control surfaces

Lift, drag, and elevator hinge moments of Handley Page control surfaces

Date: January 1, 1928
Creator: Smith, R H
Description: This report combines the wind tunnel results of tests on four control surface models made in the two wind tunnels of the Navy Aerodynamic Laboratory, Washington Navy Yard, during the years of 1922 and 1924, and submitted for publication to the National Advisory Committee for Aeronautics May 7, 1927. The purpose of the tests was to compare, first, the lifts and the aerodynamic efficiencies of the control surfaces from which their relative effectiveness as tail planes could be determined; then the elevator hinge moments upon which their relative ease of operation depended. The lift and drag forces on the control surface models were obtained for various stabilizer angles and elevator settings in the 8 by 8 foot tunnel by the writer in 1922; the corresponding hinge moments were found in the 4 by 4 foot tunnel by Mr. R. M. Bear in 1924. (author).
Contributing Partner: UNT Libraries Government Documents Department
Method of correcting wind tunnel data for omitted parts of airplane models

Method of correcting wind tunnel data for omitted parts of airplane models

Date: January 1, 1927
Creator: Smith, R H
Description: Wind tunnel models do not have complete similarity to the full scale airplane. Part of the dissimilarity is due to the difference between the stationary model in the artificial wind stream of the tunnel and the moving airplane in still air. There are a number of other reasons for departing from exact geometrical similitude. For reasons of accuracy and economy, all minor parts of the full scale airplane, such as struts, wires, fittings, control horns and other parts whose scale corrections are large are removed from wind tunnel models. By omitting the minor parts of the airplane in the wind tunnel model and adding to the forces and moments of the model those omitted parts measured full scale and properly reduced, the scale effects of such parts disappear from the model data. Scale effects due to major parts of the airplane, particularly the fuselage and wings, can be corrected by omitting the propeller and making the surface of the model as smooth as possible, two further departures from geometrical similitude between model and full scale that add considerably to the accuracy and economy of model tests.
Contributing Partner: UNT Libraries Government Documents Department
Resistance and cooling power of various radiators

Resistance and cooling power of various radiators

Date: January 1, 1928
Creator: Smith, R H
Description: This reports combines the wind tunnel results of radiator tests made at the Navy Aerodynamical Laboratory in Washington during the summers of 1921, 1925, and 1926. In all, 13 radiators of various types and capacities were given complete tests for figure of merit. Twelve of these were tested for resistance to water flow and a fourteenth radiator was tested for air resistance alone, its heat dissipating capacity being known. All the tests were conducted in the 8 by 8 foot tunnel, or in its 4 by 8 foot restriction, by the writer and under conditions as nearly the same as possible. That is to say, as far as possible, the general arrangement and condition of the apparatus, the observation intervals, the ratio of water flow per unit of cooling surface, the differential temperatures, and the air speeds were the same for all.
Contributing Partner: UNT Libraries Government Documents Department
Vapor-Pressure Chart for Volatile Hydrocarbons

Vapor-Pressure Chart for Volatile Hydrocarbons

Date: August 1942
Creator: Smith, R. Vincent
Description: Report issued by the U.S. Bureau of Mines discussing the construction of a vapor-pressure chart. A description of the vapor-pressure chart is presented. This report includes illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Transonic flutter investigation of models of the sweptback wing of a fighter airplane

Transonic flutter investigation of models of the sweptback wing of a fighter airplane

Date: April 15, 1958
Creator: Smith, Samuel L , III & Boswinkle, Robert W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Mining Industry in the Territory of Alaska During the Calendar Year 1915

The Mining Industry in the Territory of Alaska During the Calendar Year 1915

Date: 1917
Creator: Smith, Sumner S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Mining Industry in the Territory of Alaska: During the Calendar Year 1916

The Mining Industry in the Territory of Alaska: During the Calendar Year 1916

Date: 1917
Creator: Smith, Sumner S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airplane dopes and doping

Airplane dopes and doping

Date: January 1, 1919
Creator: Smith, W H
Description: Cellulose acetate and cellulose nitrate are the important constituents of airplane dopes in use at the present time, but planes were treated with other materials in the experimental stages of flying. The above compounds belong to the class of colloids and are of value because they produce a shrinking action on the fabric when drying out of solution, rendering it drum tight. Other colloids possessing the same property have been proposed and tried. In the first stages of the development of dope, however, shrinkage was not considered. The fabric was treated merely to render it waterproof. The first airplanes constructed were covered with cotton fabric stretched as tightly as possible over the winds, fuselage, etc., and flying was possible only in fine weather. The necessity of an airplane which would fly under all weather conditions at once became apparent. Then followed experiments with rubberized fabrics, fabrics treated with glue rendered insoluble by formaldehyde or bichromate, fabrics treated with drying and nondrying oils, shellac, casein, etc. It was found that fabrics treated as above lost their tension in damp weather, and the oil from the motor penetrated the proofing material and weakened the fabric. For the most part the film of ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-aspect-ratio Swept-back Wing-stability and Control

Wind-tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-aspect-ratio Swept-back Wing-stability and Control

Date: January 12, 1953
Creator: Smith, W. G.
Description: Subsonic and supersonic wind tunnel study of low aspect ratio sweptback wing tailless fighter aircraft model/stability and control.
Contributing Partner: UNT Libraries Government Documents Department
Nuclear Merchant Ship Reactor Shield Design Summary Report

Nuclear Merchant Ship Reactor Shield Design Summary Report

Date: August 1, 1959
Creator: Smith, W. R. & Turner, M. A.
Description: Abstract: "Most of the Nuclear Merchant Ship Reactor (NMSR) shield design work performed by The Babcock & Wilcox Company (B&W) is summarized. Primary and secondary shield results are presented, consistent with contractual requirements and designated design criteria. Methods of calculation and basic parameters are shown" (p. 1).
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at subsonic and supersonic speeds of a fighter model employing a low-aspect-ratio unswept wing and a horizontal tail mounted well above the wing plane - longitudinal stability and control

Wind-tunnel investigation at subsonic and supersonic speeds of a fighter model employing a low-aspect-ratio unswept wing and a horizontal tail mounted well above the wing plane - longitudinal stability and control

Date: November 15, 1954
Creator: Smith, Willard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department