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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
The gaseous explosive reaction at constant pressure : the reaction order and reaction rate

The gaseous explosive reaction at constant pressure : the reaction order and reaction rate

Date: January 1, 1931
Creator: Stevens, F W
Description: The data given in this report covers the explosive limits of hydrocarbon fuels. Incidental to the purpose of the investigation here reported, the explosive limits will be found to be expressed for the condition of constant pressure, in the fundamental terms of concentrations (partial pressures) of fuel and oxygen.
Contributing Partner: UNT Libraries Government Documents Department
The gaseous explosive reaction : the effect of inert gases

The gaseous explosive reaction : the effect of inert gases

Date: January 1, 1928
Creator: Stevens, F W
Description: Attention is called in this report to previous investigations of gaseous explosive reactions carried out under constant volume conditions, where the effect of inert gases on the thermodynamic equilibrium was determined. The advantage of constant pressure methods over those of constant volume as applied to studies of the gaseous explosive reaction is pointed out and the possibility of realizing for this purpose a constant pressure bomb mentioned. The application of constant pressure methods to the study of gaseous explosive reactions, made possible by the use of a constant pressure bomb, led to the discovery of an important kinetic relation connecting the rate of propagation of the zone of explosive reaction within the active gases, with the initial concentrations of those gases: s = K(sub 1)(A)(sup n1)(B)(sup n2)(C)(sup n3)------. By a method analogous to that followed in determining the effect of inert gases on the equilibrium constant K, the present paper records an attempt to determine their kinetic effect upon the expression given above.
Contributing Partner: UNT Libraries Government Documents Department
The gaseous explosive reaction : the effect of pressure on the rate of propagation of the reaction zone and upon the rate of molecular transformation

The gaseous explosive reaction : the effect of pressure on the rate of propagation of the reaction zone and upon the rate of molecular transformation

Date: January 1, 1932
Creator: Stevens, F W
Description: This study of gaseous explosive reaction has brought out a number of important fundamental characteristics of the explosive reaction indicating that the basal processes of the transformation are much simpler and corresponds more closely to the general laws and principles of ordinary transformations than is usually supposed. The report calls attention to the point that the rate of molecular transformation within the zone was found in all cases to be proportional to pressure, that the transformation within the zone is the result of binary impacts. This result is of unusual interest in the case of the reaction of heavy hydrocarbon fuels and the reaction mechanism proposed by the recent kinetic theory of chain reactions.
Contributing Partner: UNT Libraries Government Documents Department
Langley full-scale tunnel investigation of the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Langley full-scale tunnel investigation of the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Date: August 30, 1948
Creator: Stevens, George L & May, Ralph W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Induction-System Icing on Aircraft-Engine Operating Characteristics

Effects of Induction-System Icing on Aircraft-Engine Operating Characteristics

Date: January 20, 1947
Creator: Stevens, Howard C., Jr.
Description: An investigation was conducted on a multicylinder aircraft engine on a dynamometer stand to determine the effect of induction-system icing on engine operating characteristics and to compare the results with those of a previous laboratory investigation in which only the carburetor and the engine-stage supercharger assembly from the engine were used. The experiments were conducted at simulated glide power, low cruise power, and normal rated power through a range of humidity ratios and air temperatures at approximately sea-level pressure. Induction-system icing was found to occur within approximately the same limits as those established by the previous laboratory investigation after making suitable allowances for the difference in fuel volatility and throttle angles. Rough operation of the engine was experienced when ice caused a marked reduction in the air flow. Photographs of typical ice formations from this investigation indicate close similarity to icing previously observed in the laboratory.
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the transonic drag of models of several isolated external stores and nacelles

Flight measurements of the transonic drag of models of several isolated external stores and nacelles

Date: March 11, 1955
Creator: Stevens, Joseph E & Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models between Mach Numbers of 0.8 and 1.3, TED No. NACA DE 391

Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models between Mach Numbers of 0.8 and 1.3, TED No. NACA DE 391

Date: March 24, 1955
Creator: Stevens, Joseph E.
Description: Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test. The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to about 0.300 at a Mach number of 1.25. Increasing the total fineness ratio by a small amount raised the drag-rise Mach number slightly.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Date: January 1, 1950
Creator: Stevens, Joseph E.
Description: An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was encountered. The ratio of tip helix angle to aileron deflection indicated a decrease in proportional rolling effectiveness with increasing deflections in the Mach number range from approximately 0.7 to 1.0. A drag rise of about 125 percent in the transonic region between Mach numbers of 0.85 and 1.02 followed by a gradual decrease at higher speeds was revealed.
Contributing Partner: UNT Libraries Government Documents Department
Qualitative Results from a Flight Investigation to Determine Aileron Effectiveness of Two Rocket-Propelled 1/20-Scale Models of the MX -76 Missile

Qualitative Results from a Flight Investigation to Determine Aileron Effectiveness of Two Rocket-Propelled 1/20-Scale Models of the MX -76 Missile

Date: October 20, 1955
Creator: Stevens, Joseph E.
Description: Free-flight tests of two rocket-propelled l/20-scale models of the Bell MX-776 missile have been conducted to obtain measurements of the aileron deflection required to counteract the induced rolling moments caused by combined angles of attack and sideslip and thus to determine whether the ailerons provided were capable of controlling the model at the attitudes produced by the test conditions. Inability to obtain reasonably steady-state conditions and superimposed high-frequency oscillations in the data precluded any detailed analysis of the results obtained from the tests. For these reasons, the data presented are limited largely to qualitative results.
Contributing Partner: UNT Libraries Government Documents Department
A survey of background and aircraft noise in communities near airports

A survey of background and aircraft noise in communities near airports

Date: December 1, 1954
Creator: Stevens, K N
Description: None
Contributing Partner: UNT Libraries Government Documents Department