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Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Description: "The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel in… more
Date: July 28, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Chemical and physical factors affecting combustion in fuel-nitric acid systems

Description: Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chem… more
Date: July 28, 1958
Creator: Baker, Louis, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Three Injectors in a 2400-Pound-Thrust Rocket Engine Using Liquid Oxygen and Liquid Ammonia

Description: Report presenting the performance of three injector types in a 2400-pound-thrust rocket test chamber. Characteristic velocity and specific impulses were obtained over a range of oxidant-to-fuel ratios at a nominal chamber pressure of 600 pounds per square inch absolute. RMI-1 and 2 had fairly similar results, but RMI-3 gave no stabilized data due to combustion instability.
Date: July 28, 1958
Creator: Hendricks, Robert C.; Ehlers, Robert C. & Humphrey, Jack C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Prototype Iroquois Turbojet Engine in an Altitude Test Chamber Coord. No. AF-P-6

Description: "Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors" (Abstract).
Date: July 28, 1958
Creator: McAulay, John E. & Groesbeck, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering

Description: Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.
Date: July 28, 1958
Creator: Kinard, William H. & Lambert, C. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering

Description: Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.
Date: July 28, 1958
Creator: Kinard, William H. & Lambert, C. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile

Description: "A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).
Date: May 28, 1958
Creator: Hall, James R. & Garland, Benjamine J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials

Description: Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models coo… more
Date: May 28, 1958
Creator: Modisette, Jerry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials

Description: Report presenting testing of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. The models were tested in the ceramic-heated jet at a Mach number of 2, a stagnation temperature of 4,000 degrees Fahrenheit, and a stagnation pressure of 105 lb/sq. in. abs. Lithium hydride offers significant cooling for the materials while magnesium shows a slight cooling.
Date: May 28, 1958
Creator: Modisette, Jerry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Local Isotropy in Turbulent Shear Flow

Description: "The mean strain rate in turbulent shear flow must tend to make the structure anisotropic in all parts of the spectrum. It is argued here, however, that if the spectral energy transfer process destroys orientation, the Kolmogoroff notion of local isotropy can still be justified in spectral regions where the local transfer time is shorter than the characteristics time of the gross shear strain" (p. 1).
Date: May 28, 1958
Creator: Corrsin, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of High-Speed Impact the Penetration of Small Spheres Into Thick Copper Targets

Description: Small metal spheres of various densities were fired at high speed into thick targets of copper and lead. In general, it was found that all of the penetrations could be correlated quite well for engineering purposes by a function relating the depth of penetration to the impact momentum per unit volume.
Date: May 28, 1958
Creator: Charters, A. C. & Locke, G. S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel

Description: Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date: May 28, 1958
Creator: Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel

Description: Report presenting force-oscillation testing in the transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Tests were performed at a variety of Mach numbers, reduced frequencies, and tunnel stagnation pressures, but at a constant oscillating amplitude. Results regarding aerodynamic damping, aerodynam… more
Date: May 28, 1958
Creator: Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Various Heat Exchangers for Liquid-Metal Nuclear Turbojet Over Range of Flight and Operating Conditions

Description: Memorandum presenting an analysis of a large number of liquid-metal-to-air heat-exchanger cores for the nuclear-powered liquid-metal turbojet cycle to determine which types yield the best overall net thrust per total engine weight. The performances of all exchangers considered were initially evaluated at a median condition. The performance of the best of each of the four types was compared with that of a shell-and-tube exchanger with the air flowing through the tubes, operating at the same cond… more
Date: April 28, 1958
Creator: Ragsdale, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of wing-mounted external stores on the longitudinal and lateral handing qualities of the Douglas D-558-II research airplane

Description: Report presenting testing of the subsonic and transonic handling qualities of the Douglas D-558-II research airplane using several configurations of mid-semispan external stores in the altitude region of 20,000 to 40,000 feet. The configurations had an underslung pylon on each wing, pylons plus simulated 1000-pound bombs, and pylons with 150-gallon fuel tanks. Results regarding longitudinal stability and control characteristics, low-speed characteristics, and lateral stability and control chara… more
Date: October 28, 1957
Creator: Fischel, Jack; Darville, Robert W. & Reisert, Donald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static lateral characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations

Description: Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a wing-chord-plane tail, a T tail, and a biplane tail. A discussion regarding the lateral derivatives and sideslip characteristics is provided.
Date: October 28, 1957
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Three Aluminum-Alloy Models and One Steel Model of 20-Inch Chord and Span With Various Internal Structures and Skin Thicknesses

Description: Report presenting testing of four multiweb wing structures similar to those on an airplane or missile at Mach number 2, sea-level static pressure, a 0 degree angle of attack, and stagnation temperature of 500 degrees Fahrenheit. Three models were made of 2024-T3 aluminum alloy and one was made from SAE 1010 steel; internal structure and skin thickness varied across the models. Results regarding model behavior, model temperatures, calculated skin temperatures, strain-gage results, model pressure… more
Date: October 28, 1957
Creator: Rosecrans, Richard; Vosteen, Louis F. & Batdorf, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064-Inch-Thick Skin at Angles of Attack of 0 Degree and Plus or Minus 2 Degrees

Description: Report presenting testing of two identically constructed 2024-T3 aluminum-alloy multiweb-wing structures, models MW-2-(2) and MW-2-(3), under aerodynamic conditions similar to those encountered in supersonic flight at Mach number 2. Results regarding model temperatures, Stanton number, model pressures, model strains, behavior of Model MW-2-(2), and behavior of Model MW-2-(3) are provided.
Date: October 28, 1957
Creator: Miltonberger, Georgene H.; Griffith, George E. & Davidson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio

Description: "Slender-body aerodynamic theory is used in conjunction with thin-plate theory in the flutter analysis of low-aspect-ratio rectangular wings of constant thickness when chordwise variations of deflections are considered. The spanwise variation of deflection is given by a parabola, and the chordwise variation is allowed complete freedom. The results show the variation of flutter speed and mode shape with aspect ratio" (p. 1).
Date: June 28, 1957
Creator: Fralich, Robert W.; Hedgepeth, John M. & Tuovila, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Cascade Investigation of Thin Low-Camber Naca 65-Series Blade Sections at High Inlet Angles

Description: Report presenting an investigation of 6-percent-thick NACA 65-series compressor blade sections in a two-dimensional porous-wall cascade tunnel at several lift coefficients, angles of attack, and solidities. The useful operating angle-of-attack range was generally found to decrease as inlet angle increases.
Date: June 28, 1957
Creator: Emery, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-Scale 49 Degree Swept Wing-Body-Tail Configuration in Combination With a Drooped Nose and a Nose With a Radius Increase

Description: "A 49 degree swept-wing complete model equipped for high-pressure blowing full span at two chordwise locations at the leading edge of a full-span wing and over a half-span flap has been tested in the Langley full-scale tunnel to determine the effectiveness of blowing at the leading edge as a supplementary leading-edge stall control at high lift coefficients." The effect of blowing on the lift characteristics, pitching-moment characteristics, and drag characteristics of this particular model is … more
Date: May 28, 1957
Creator: Fink, Marvin P. & McLemore, H. Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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