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Effect of Fuel Composition, Engine Operating Variables, and Spark-Plug Type and Condition on Preignition-Limited Performance of an R-2800 Cylinder

Description: The preignition characteristics of the R-2800 cylinder, as effected by fuel consumption, engine operating variables, and spark plug type and condition, were evaluated. The effects on preignition-limited performance of various percentages of aromatics (benzene, toluene, cumene, xylene) in a base fuel of triptane were investigated. Two paraffins (triptane and S + 6.0 ml TEL/gal) and two refinery blends (28-R and 33-R) were preignition rated. The effect of changes in the following engine operating… more
Date: November 15, 1946
Creator: Pfender, John F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Tests of a Burner for Ram-Jet Applications

Description: "Preliminary tests have been made of a small burner to meet the requirements for application to supersonic ram jets. The principal requirements were taken as: (1) efficient combustion in a high-velocity air stream, (2) utilization for combustion of only a small fraction of the air passing through the unit, (3) low resistance to air flow, (4) simple construction, and (5) light weight. Tests of a small burner were carried to stream velocities of nearly 150 feet per second and fuel rates such that… more
Date: January 15, 1947
Creator: Huber, Paul W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Langley full-scale-tunnel investigation of the factors affecting the static lateral-stability characteristics of a typical fighter-type airplane

Description: "The factors that affect the rate of change of rolling moment with yaw of a typical fighter-type airplane were investigated in the Langley full-scale tunnel on a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate effects of propeller operation, of the wing-fuselage combination, and of the vertical tail to the effective dihedral of the airplane in each condition were determined. The results of the tests showed that for the airplane wit… more
Date: April 15, 1947
Creator: Lange, Roy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compilation of Test Data on 111 Free-Spinning Airplane Models Tested in the Langley 15-Foot and 20-Foot Free-Spinning Tunnels

Description: "A compilation of free-spinning-airplane model data on the spin and recovery characteristics of 111 airplanes is presented. These data were previously published in separate memorandum reports and were obtained from free-spinning tests in the Langley 15-foot and the Langley 20-foot free-spinning tunnels. The model test data presented include the steady-spin and recovery characteristics of each model for various combinations of aileron and elevator deflections and for various loadings and dimensi… more
Date: May 15, 1947
Creator: Malvestuto, Frank S., Jr.; Gale, Lawrence J. & Wood, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of 10-Stage Axial-Flow X24C-2 Compressor, 1, Performance at Inlet Pressure of 21 Inches Mercury Absolute and Inlet Temperature of 538 Degrees R

Description: The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived.
Date: July 15, 1947
Creator: Schum, Harold J. & Buckner, Howard A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models

Description: Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date: July 15, 1947
Creator: Jessen, Henry, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Description: Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain opera… more
Date: August 15, 1947
Creator: Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a Preloaded Spring-Tab Flutter Model

Description: "An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one" (p. 1).
Date: December 15, 1947
Creator: Smith, N. H.; Clevenson, S. A. & Barmby, J. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail

Description: "Low-speed wind-tunnel tests of a l/8 scale model of the Republic XP-91 airplane were made to determine its low-speed characteristics and the relative merits of a vee and a conventional tail on the model. The results of the tests showed that for the same amount of longitudinal and directional stability the conventional tail gave less roll due to sideslip than did the vee tail. The directional stability of the model was considered inadequate for both the vee and conventional tails; however, incr… more
Date: December 15, 1947
Creator: Weiberg, James A. & Anderson, Warren E.
Item Type: Refine your search to only 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

Description: 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: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: D-588-1 Speed-Reduction Brake and Symmetrical-Profile Wing Characteristics

Description: Report presenting the results of pitching-moment, lift, and drag measurements on a model of the D-558-1 with speed reduction brakes and a symmetrical profile wing at a range of Mach numbers. Only a small decrement in Mach number is produced with no nose-inlet flow and the speed-reduction brakes deflected.
Date: June 15, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers 1: shock diffuser with triple-shock projecting cone

Description: Report presenting an investigation in the 20-inch supersonic tunnel at Mach number 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems. Results regarding diffuser performance with combustion, combustion with constant outlet-inlet area ratio, combustion with constant fuel flow, diff… more
Date: September 15, 1948
Creator: Connors, J. F. & Schroeder, A. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Pressure Distribution on Fuselage Nose and Pilot Canopy of Supersonic Airplane at Mach Number 1.90

Description: An investigation of the pressure distribution on the fuselage nose and the pilot canopy of a supersonic airplane model has been conducted at a Mach number of 1.90 over a wide range of angles of attack and yaw. Boundary layer separation apparently occurred from the upper surface at angles of attack above 24 degrees and from the lower surface at minus 15 degrees. No separation from the sides of the fuselage was evident at yaw angles up to 12 degrees.
Date: October 15, 1948
Creator: Wyatt, DeMarquis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a variable Mach number supersonic tunnel with nonintersecting characteristics

Description: Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls. Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are provided.
Date: November 15, 1948
Creator: Evvard, John C. & Wyatt, DeMarquis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of Sweep on the Flutter of Cantilever Wings

Description: Report presenting an experimental and analytical investigation of the flutter of uniform sweptback cantilever wings. The experiments used groups of wings sweptback by rotating and by shearing with angles of sweep ranging from 0 to 60 degrees. Results regarding the experimental investigation and a discussion and comparison of the analytical and experimental results are provided.
Date: November 15, 1948
Creator: Barmby, J. G.; Cunningham, H. J. & Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and control characteristics of a free-flying model with an unswept wing of aspect ratio 3 (XS-3)

Description: The results of power-off force tests and flight tests of a model with a thin unswept low-aspect-ratio wing are presented. The tests were made with the flaps retracted and deflected. The effects on the lateral flight characteristics of decreasing directional stability were noted.
Date: November 15, 1948
Creator: Bennett, Charles V. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Allison Model 400-C6 Turbojet-Engine Compressor, 1: Over-All Performance Characteristics of Compressor at Equivalent Impeller Speeds of 6000, 7000, and 8500 RPM

Description: The Allison model 400-C6 compressor was operated at an inlet pressure of 12 inches of mercury absolute ana ambient inlet temperature at equivalent impeller speeds of 6000, 7000, and 8500 rpm. Additional runs at an equivalent speed of 7000 rpm and ambient inlet temperature were made at inlet pressures from 7 to 22 inches of mercury absolute. The results of this investigation are compared with those of the 533-A-23 compressors. For the speeds investigated, the Allison model 400-C6 compressor had … more
Date: December 15, 1948
Creator: Kovach, Karl & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw

Description: Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
Date: February 15, 1949
Creator: Crigler, John L. & Gilman, Jean, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 4: some effects of internal duct shape upon an inlet enclosing 37.2 percent of the forebody circumference

Description: Report presenting tests to determine the recovery of total pressure attainable at a range of Mach numbers, which were performed with models with twin-scoop inlets situated on the sides of a long forebody. Results regarding ducts without slots and ducts with slots are provided.
Date: March 15, 1949
Creator: Davis, Wallace F.; Edwards, Sherman S. & Brajnikoff, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane

Description: Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date: April 15, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of the Availability and Performance Problems of High Octane Number Fuels

Description: Memorandum presenting a study to determine the possible blending agents or additives that may be used to supplement current high performance number, rich rating components in future aviation fuels. The study indicated that such high rich rating blending agents as toluene and xylene cannot be made available in sufficient quantities to maintain the rich rating performance of the fuels when reducing the lead content from 4.6 to 3.0 ml per gallon.
Date: April 15, 1949
Creator: NACA Committee on Aircraft Fuels
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of piston-type gas-generator engine for subsonic transport operation

Description: Report presenting an evaluation of a piston-type gas-generator engine by comparing the performance of a transport airplane powered with than engine with the same airplane powered by different engines. The engines compared were a turbojet engine, a turbine-propeller engine, a compound engine, and a turbosupercharged reciprocating engine utilizing a variable-area exhaust jet nozzle. Results regarding optimum altitude and transport performance are provided.
Date: July 15, 1949
Creator: Lietzke, A. F. & Henneberry, Hugh M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date: August 15, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine

Description: Report presenting an investigation of the experimental performance of chlorine triflouride and hydrazine measured over a range of propellant mixtures in a 100-pound-thrust rocket engine. Experimental values of specific impulse, volume specific impulse, heat rejection per propellant weight, nozzle thrust coefficient, and characteristic velocity were obtained as functions of percent fuel by weight in the propellant mixture.
Date: August 15, 1949
Creator: Ordin, Paul M. & Miller, Riley O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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