Resource Type

States

De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding (open access)

De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding

Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date: May 25, 1953
Creator: Ruggeri, Robert S.
Object Type: Report
System: The UNT Digital Library
Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating (open access)

Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

"An investigation was made to determine the static lateral stability and control characteristics of a 1/6-scale model of the Republic XF-84H airplane with the propeller operating. The model had a 40 degree swept wing of aspect ratio 3.45 and had a thin 3-blade supersonic-type propeller. Many modifications to the basic configuration were investigated in attempts to alleviate lateral and directional trim problems which appeared to be associated with propeller slipstream rotation" (p. 1).
Date: June 25, 1953
Creator: Sleeman, William C., Jr. & Morrison, William D., Jr.
Object Type: Report
System: The UNT Digital Library
A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds (open access)

A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds

From Summary: "A simplified analysis is made of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds. It is found that, in general, the gravity force is negligible compared to the aerodynamic drag force and, hence, that the trajectory is essentially a straight line. A constant drag coefficient and an exponential variation of density with altitude are assumed and generalized curves for the variation of missile speed and deceleration with altitude are obtained. A curious finding is that the maximum deceleration is independent of physical characteristics of a missile (e.g., mass, size, and drag coefficient) and is determined only by entry speed and flight-path angle, provided this deceleration occurs before impact. This provision is satisfied by missiles presently of more usual interest."
Date: August 25, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Object Type: Report
System: The UNT Digital Library
Preliminary Appraisal of Ferrocene as an Igniting Agent for JP-4 Fuel and Fuming Nitric Acid (open access)

Preliminary Appraisal of Ferrocene as an Igniting Agent for JP-4 Fuel and Fuming Nitric Acid

From Summary: "A preliminary experimental study was made of the properties of ferrocene as a solute and as a suspension in JP-4 fuel, and of the ignition delays of ferrocene - JP-4 mixture with A.F. specification 14104 white fuming nitric acid (WFNA). The investigation covered concentrations of 4 to 10 percent by weight ferrocene, and a temperature range of -40 to 80 F. The solubility of ferrocene in JP-4 is about 5 percent at room temperature and about 1 percent (extrapolated) at -80 F. The solubility is increased somewhat by increased aromatics content. Undissolved ferrocene particles of 100 mesh and smaller settle rapidly in JP-4."
Date: August 25, 1953
Creator: Miller, Riley O.
Object Type: Report
System: The UNT Digital Library
Effects of slot location and geometry on the flow in a square tunnel at transonic Mach numbers (open access)

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

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.
Object Type: Report
System: The UNT Digital Library
Comparison of the experimental and theoretical distribution of lift on a slender inclined body of revolution at M = 2 (open access)

Comparison of the experimental and theoretical distribution of lift on a slender inclined body of revolution at M = 2

From Summary: "Pressure distributions and force characteristics have been determined for a body of revolution consisting of a fineness ratio 5.75, circular-arc, ogival nose tangent to a cylindrical afterbody for an angle-of-attack range of 0 degrees to 35.5 degrees. The free-stream Mach number was 1.98 and the free-stream Reynolds number was approximately 0.5 x 10 sup 6, based on body diameter. Comparison of the theoretical and experimental pressure distributions shows that for zero lift, either slender-body theory or higher-order theories yield results which are in good agreement with experiment."
Date: August 25, 1953
Creator: Perkins, Edward W. & Kuehn, Donald M.
Object Type: Report
System: The UNT Digital Library
Some observations on stall flutter and buffeting (open access)

Some observations on stall flutter and buffeting

"An attempt is made to describe the phenomenological differences between stall flutter and buffeting. Some experimental results are presented concerning both the boundaries at which these phenomena occur and the stresses involved" (p. 1).
Date: June 25, 1953
Creator: Rainey, A. Gerald
Object Type: Report
System: The UNT Digital Library
Effect of Variations in Reynolds Number on the Aerodynamic Characteristics of Three Bomb or Store Shapes at a Mach Number of 1.62 With and Without Fins (open access)

Effect of Variations in Reynolds Number on the Aerodynamic Characteristics of Three Bomb or Store Shapes at a Mach Number of 1.62 With and Without Fins

Memorandum presenting tests in the 9-inch supersonic tunnel of three bomb or store shapes without fins and with two sets of cruciform fins. Measurements of normal force, chord force, and pitching moment were made; analyses of the effects of angle of attack and Reynolds number on these qualities and also upon center-of-pressure position and fin effectiveness are presented.
Date: June 25, 1953
Creator: Rainey, Robert W.
Object Type: Report
System: The UNT Digital Library
Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds (open access)

Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds

Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.
Date: June 25, 1953
Creator: Spahr, J. Richard & Dickey, Robert R.
Object Type: Report
System: The UNT Digital Library
Weight Bar Charts (open access)

Weight Bar Charts

The weight breakdowns in bar chart form in the present report have been prepared to give an indication of 'how we spend our weight.' They are expected to focus attention on the design functions that warrant weight reduction activity on future models.
Date: June 25, 1953
Creator: Saelman, B. J. & Vick, H. W.
Object Type: Report
System: The UNT Digital Library
Preliminary Investigation of a Variable-Area Auxiliary Air-Intake System at Mach Numbers From 0 to 1.3 (open access)

Preliminary Investigation of a Variable-Area Auxiliary Air-Intake System at Mach Numbers From 0 to 1.3

"A variable-area auxiliary air scoop in combination with a fixed-area nose intake was tested at Mach numbers from 0 to 1.3. The purpose of the investigation was to evaluate the effectiveness of such an auxiliary intake in improving the net thrust of an intake-engine combination over a range of speeds. The results indicated that the internal flow was always stable and that improvements in net thrust would be realized at Mach numbers up to about 1.1 for an intake design Mach number of 1.3" (p. 1).
Date: February 25, 1953
Creator: Scherrer, Richard; Stroud, John F. & Swift, John T.
Object Type: Report
System: The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail (open access)

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail

Report presenting an investigation to determine the low-speed, large-scale characteristics of an airplane configuration with an aspect ratio 2 triangular wing of variable incidence. The model consisted of the variable-incidence wing in combination with a fuselage of fineness ratio 13, a triangular vertical tail, and a thin, unswept, all-movable horizontal tail. Results regarding the lift characteristics of the model with the tail off, longitudinal stability with the horizontal tail on, trim lift and drag characteristics, and directional instability are provided.
Date: June 25, 1953
Creator: Koenig, David G.
Object Type: Report
System: The UNT Digital Library
Flight Measurement of Aerodynamic Loads and Moments on an External Store Mounted Under the Wing of a Swept-Wing Fighter-Type Airplane (open access)

Flight Measurement of Aerodynamic Loads and Moments on an External Store Mounted Under the Wing of a Swept-Wing Fighter-Type Airplane

Report discussing an investigation of external-store characteristics using a 245-gallon external fuel tank mounted under a wing of a North American F-86A airplane. The store normal force was found to increase abruptly on penetration of the buffet boundary. Information about the normal- and side-load distribution and integrated force and moment coefficients is provided.
Date: November 25, 1953
Creator: O'Bryan, Thomas C.
Object Type: Report
System: The UNT Digital Library
Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing (open access)

Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing

Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.
Date: March 25, 1953
Creator: Mueller, James N.
Object Type: Report
System: The UNT Digital Library
Free-Jet Altitude Investigation of a 20-Inch Ram-Jet Combustor With a Rich Inner Zone of Combustion for Improved Low-Temperature-Ratio Operation (open access)

Free-Jet Altitude Investigation of a 20-Inch Ram-Jet Combustor With a Rich Inner Zone of Combustion for Improved Low-Temperature-Ratio Operation

From Summary: "An investigation of the altitude performance of a 20-inch-diameter high-temperature-ratio ram-jet combustor which had been redesigned to provide good combustor efficiency over a wide range of temperature ratios was conducted at zero angle of attack in a free-jet facility at a Mach number of 3.0. Configurations investigated incorporated a cylindrical control sleeve which confined the injected fuel at low over-all fuel-air ratios to about 40 percent of the engine air flow. This provided an optimum fuel-air mixture over a portion of the flame holder when the over-all fuel-air ratio was about 0.02."
Date: May 25, 1953
Creator: Trout, Arthur M. & Wentworth, Carl B.
Object Type: Report
System: The UNT Digital Library
Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine (open access)

Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine

Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.
Date: May 25, 1953
Creator: Conrad, E. William; Finger, Harold B. & Essig, Robert H.
Object Type: Report
System: The UNT Digital Library
Applications of auxiliary air injectors to supersonic wind tunnels (open access)

Applications of auxiliary air injectors to supersonic wind tunnels

Report presenting a discussion of the adverse effects of high compression ratio requirements for supersonic wind tunnels as well as the use of second throats for alleviating those effects. The results indicated that an auxiliary air-injector system can reduce starting and running compression ratios as compared to a conventional wind tunnel with a divergent diffuser.
Date: November 25, 1953
Creator: Spiegel, Joseph M.; Hofstetter, Robert U. & Kuehn, Donald M.
Object Type: Report
System: The UNT Digital Library
De-icing and runback characteristics of three cyclic electric, external de-icing boots employing chordwise shedding (open access)

De-icing and runback characteristics of three cyclic electric, external de-icing boots employing chordwise shedding

Report presenting an icing investigation conducted in the icing research tunnel to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The boots were all designed for the same airplane and were designed to operate at the same values of power density, heat-on time, and cycle ratio. Results regarding the boot surface temperatures and general de-icing and runback characteristics are provided.
Date: May 25, 1953
Creator: Ruggeri, Robert S.
Object Type: Report
System: The UNT Digital Library
Texas Attorney General Opinion: S-10 (open access)

Texas Attorney General Opinion: S-10

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Authority of tax assessor and collector to maintain an office in Whitesboro.
Date: February 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: S-11 (open access)

Texas Attorney General Opinion: S-11

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Eligibility of the Texas Municipal Retirement System to receive funds appropriated for the Firemen's Relief and Retirement Fund.
Date: February 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: S-113 (open access)

Texas Attorney General Opinion: S-113

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Payment of poll tax as a prerequisite to voting by servicemen during 1954.
Date: November 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: MS-41 (open access)

Texas Attorney General Opinion: MS-41

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Constitutionality of Senate Bill 29, Acts 53rd Legislature.
Date: May 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: MS-42 (open access)

Texas Attorney General Opinion: MS-42

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Authority of the Board of Hairdressers and Cosmetologists under House Bill No. 79 to exercise more control over its funds than would be authorized by the General Appropriation Bill.
Date: May 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: MS-65 (open access)

Texas Attorney General Opinion: MS-65

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Authority of Banking Commissioner to approve location of the Brazosport Savings & Loan Association at Velasco.
Date: June 25, 1953
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History