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Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Description: Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coe… more
Date: November 30, 1956
Creator: Turner, Kenneth L. & Fournier, Roger H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compilation and Analysis of U.S. Turbojet and Ram-Jet Engine Characteristics

Description: Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.
Date: November 27, 1956
Creator: Cesaro, Richard S. & Walker, Curtis L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System

Description: Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible t… more
Date: November 23, 1956
Creator: Douvillier, Joseph G., Jr.; Foster, John V. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications

Description: Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thermal Stability of Decaborane and of a Commercial Ethyl Decaborane (HEF-3) in the Range 202 Degrees to 252 Degrees C

Description: Report discussing an investigation of the thermal stabilities of a commercial grade of ethyl decaborane and decaborane at two temperatures. Equations developed from the results of the experiment are also provided. Ethyl decaborane was found to be more stable to pyrolysis than pentaborane but less stable than decaborane.
Date: November 29, 1956
Creator: McDonald, G. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a High Subsonic Mach Number Turbine Having High Rotor Blade Suction-Surface Diffusion

Description: Memorandum presenting a high subsonic Mach number turbine with high suction-surface diffusion investigated experimentally. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub input.
Date: November 20, 1956
Creator: Nusbaum, William J. & Hauser, Cavour H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Description: Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.
Date: November 20, 1956
Creator: Breitwieser, Roland & Useller, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 with area suction applied to trailing-edge flaps and with several wing leading-edge modifications

Description: Report presenting an investigation of an airplane model conducted to determine the effect of area-suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. Results regarding the effect of trailing-edge flaps on the aerodynamic characteristics of the model with horizontal tail off, effect of wing modifications on the high-lift characteristics of the model with the horizontal tail off, aerodynamic characteristics of the mo… more
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed measurements of tail contribution to rolling stability derivatives and air-flow angularity at the tail for an x-tail model in steady roll including some effects of wing-tip stores

Description: Report presenting an investigation in the stability tunnel to determine the combined effect of wing and wing-body interference on the contribution of an x-tail configuration to the low-speed rolling-stability derivatives of an airplane model with an unswept midwing and to indicate the change due to roll in the local flow angularity at a number of stations across the tail surfaces for one-half of the x-tail. Results regarding the static longitudinal characteristics, steady-roll characteristics, … more
Date: November 23, 1956
Creator: Riley, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-Scale Turbojet Engine

Description: This report summarizes the full-scale engine tests of pentaborane, pentaborane - JP-4 fuel mixtures, and trimethylborate azeotrope fuel. The tests were conducted in a full-scale turbojet engine at a simulated altitude of 50,000 feet and Mach number of 0.08. Engine speeds were 90 to 100 percent of rated speed. Pentaborane reduced the the specific fuel consumption to two-thirds that of JP-4 fuel. However, because boron oxide collected in the engine, the performance deteriorated with continued ope… more
Date: November 20, 1956
Creator: Breitwieser, Roland & Useller, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Methods for measuring temperatures of thin-walled gas-turbine blades

Description: The accuracy and durability of two means for measuring the metal temperature of gas-turbine blades were investigated experimentally in a turbojet engine. Cemented thermocouples that could be placed in walls as thin 0.010 inch and commercial temperature-indicating paints were evaluated at turbine-inlet temperatures up to about 1650 degrees F and for centrifugal forces equivalent to about 42,000 times gravity. The cemented thermocouples operated satisfactorily. The temperature-indicating paints w… more
Date: November 2, 1956
Creator: Stepka, Francis S. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing loads and load distributions throughout the lift range of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the left wing of the Douglas X-3 to determine the effects of angle of attack and Mach number on the wing characteristics at transonic Mach numbers. The wing had an aspect ratio of 3.09 and a modified 4.5-percent-thick hexagonal section. Data covered a range of lift values and Mach numbers.
Date: November 9, 1956
Creator: Keener, Earl R. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the vertical-tail loads measured during a flight investigation of the Douglas X-3 research airplane

Description: From Summary: "Results are presented of an analysis of the strain-gage measurements of vertical-tail loads experienced in rudder pulses, gradually increasing sideslips, and rudder-fixed aileron rolls at transonic speeds with the Douglas X-3 research airplane."
Date: November 9, 1956
Creator: Marcy, William L.; Stephenson, Harriet J. & Cooney, Thomas V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of Guy alloy as a turbojet-engine bucket material for use at 1650 degrees F

Description: As-cast buckets of Guy alloy, a cast nickel-base material, were run in a J33-9 turbojet engine for cycles of 15 minutes at rated speed and 5 minutes at idle speed. Stress rupture, impace and engine-performance data indicate that Guy alloy may be considered for bucket use at a temperature of 1650 degrees F. Ductility and impact strength of Guy alloy is limited but appears to be adequate for bucket applications.
Date: November 29, 1956
Creator: Signorelli, R. A.; Johnston, J. R. & Weeton, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Coking of JP-4 fuels in electrically heated metal tubes

Description: A limited exploratory investigation of the rate of coking of four JP-4 fuels in electrically heated metal tubes was conducted in order to provide design information for fuel prevaporizers for turbojet-engine combustors. The fuels tested included two production and two minimum-quality JP-4 type fuels. The heating tube was operated at fuel pressures of approximately 500, 400, and 50 pounds per square inch. The operating fuel temperature was varied between approximately 600 degrees and 1200 degree… more
Date: November 20, 1956
Creator: Smith, Arthur L.; Cook, William P. & Hlavin, Vincent F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static lateral and directional stability and control characteristics of revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01: COORD No. AF-163

Description: Report presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.41 and 2.01 to determine the static lateral and directional stability and control characteristics of a scale model of the Republic F-105 airplane. Results regarding the static lateral and directional stability and lateral and directional control are provided.
Date: November 19, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic Model Investigation of Two Tail-Sitter Vertically Rising Airplanes to Determine the Altitude Required to Approach Normal Flight Conditions Under Power Failure in Hovering Flight

Description: "An investigation has been undertaken on two dynamic models simulating 1/20-scale and 1/25-scale models of propeller-driven tail-sitter vertically rising airplanes to determine the altitude required to approach normal-flight conditions after power failure in hovering flight. The results of the investigation indicated that, for the two models investigated, an altitude of 3,600 to 5,400 feet may be required to attain normal gliding flight" (p. 1).
Date: November 9, 1956
Creator: Klinar, Walter J. & Wilkes, L. Faye
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation at Mach numbers between 0.5 and 1.7 of the zero-lift rolling effectiveness and drag of various surface, spoiler, and jet controls on an 80 degree delta-wing missile

Description: Report presenting a free-flight investigation of the zero-lift rolling effectiveness and drag of 18 roll-control arrangements on a cruciform 80 degree delta-wing missile-like configuration over a range of Mach numbers. Testing was made of deflected surfaces, spoilers, and inlet-air-jet devices to give evidence to simple theory for deflected surfaces and to determine some effects of chordwise location for spoilers and blowing direction and spanwise location for jets near the wing trailing edge. … more
Date: November 29, 1956
Creator: Schult, Eugene D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed pressure-distribution investigation of a thin-delta-wing-fuselage model with double slotted flap, extended double slotted flap, and canard

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60 degree delta-wing-fuselage model equipped with double slotted and extended double slotted flaps. The effects of a canard on the loads of the wing with the extended double slotted flaps are also determined.
Date: November 23, 1956
Creator: Croom, Delwin R. & Huffman, Jarrett K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Semigraphical Method for the Determination of the Rolling Characteristics of Rolleron-Equipped Missiles

Description: "A semigraphical analysis method has been devised to evaluate the effectiveness and dynamic stability of rolleron roll-rate dampers on missile configurations. The necessary charts, equations, and the analysis procedure have been presented. The greatest utility of these charts and of the method outlined is that, once a point on the charts has been established at a given flight condition, if the response is not acceptable than the necessary modifications to the parameters of the system are readil… more
Date: November 29, 1956
Creator: Nason, Martin L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a high subsonic Mach number turbine having high rotor blade suction-surface diffusion

Description: Report presenting an experimental investigation of a high subsonic Mach number turbine with high suction-surface diffusion. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub inlet.
Date: November 20, 1956
Creator: Nusbaum, William J. & Hauser, Cavour H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at Supersonic Speeds of the Effects of Bomb-Bay Configuration Upon the Aerodynamic Characteristics of Fuselages With Noncircular Cross Sections

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moments of typical body-bomb-bay configurations with and without the bomb. The bodies had elliptical, triangular, and teardrop cross sections. Results regarding effects of angle-of-attack variation and effects of Mach number variation are provided.
Date: November 29, 1956
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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