5,163 Matching Results

Search Results

Exploratory materials and missile-nose-shape tests in a 4,000 degrees F supersonic air jet

Description: Report presenting some exploratory materials and nose-shape tests in a small supersonic air jet with a stagnation temperature of approximately 4000 degrees Fahrenheit. Materials considered included graphite, copper, carbon steel, and stainless steel, and the nose shapes included 90 degree total-angle cones, hemispherical-face cylinders, and flat-face cylinders. The aerodynamic heat transfer to flat-face cylinders is appreciably less than to hemispherical-face cylinders.
Date: December 13, 1956
Creator: Purser, Paul E. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

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

Description: Report presenting drag measurements on models of 20 isolated external stores and nacelles flown from the helium gun at a range of Mach numbers. Results regarding fineness-ratio and shape effects, drag correlation, and friction drag are provided. Generally, the shape variations among the various types of stores and nacelles had the expected effects on isolated body drag.
Date: March 11, 1955
Creator: Stevens, Joseph E. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Flight measurements of wing loads on the Convair XF-92A delta-wing airplane

Description: Report presenting a flight investigation at a range of altitudes to determine the wing loads on the Convair XF-92A airplane over the lift range of the airplane at subsonic and transonic speeds. Theoretical lift-curve slope for a delta wing was calculated and compared with the flight data at a Mach number of 0.75.
Date: May 25, 1955
Creator: Kuhl, Albert E. & Johnson, Clinton T.
Partner: UNT Libraries Government Documents Department

Flight measurements of the effects of surface condition on the supersonic drag of fin-stabilized parabolic bodies of revolution

Description: Report presenting testing of rocket-powered models at supersonic speeds to determine some of the surface conditions on the zero-lift drag of fin-stabilized parabolic bodies of revolution. Two types of models and three types of surface roughness were tested. Results regarding mean-drag coefficients, side-pressure coefficients, and total-drag coefficients are provided.
Date: May 2, 1952
Creator: Jackson, H. Herbert
Partner: UNT Libraries Government Documents Department

Flight investigation at low angles of attack to determine the longitudinal stability and control characteristics of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose at Mach numbers from 1.2 to 2.1

Description: Report presenting testing of a full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Static and dynamic longitudinal stability and control derivatives were determined at low angles of attack and for a range of Mach numbers.
Date: September 30, 1957
Creator: Brown, Clarence A., Jr.
Partner: UNT Libraries Government Documents Department

Comparison of low-lift drag at Mach numbers from 0.74 to 1.37 of rocket-boosted models having externally braced wings and cantilever wings

Description: Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.
Date: September 25, 1957
Creator: Dickens, Waldo L. & Hastings, Earl C., Jr.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of transpiration cooling to alleviate aerodynamic heating on an 8 degree cone in a free jet at a Mach number of 2.05

Description: Report presenting testing of the effectiveness of transpiration cooling of an 8 degree total angle conical body with water removed onto the surface through a porous section near the nose. Results regarding a reference test without cooling, a cooling test with 0.010 pound of water per second, a cooling test with 0.0025 pound of water per second, a hypothesis of the phenomena of liquid transpiration cooling, water consumption are provided.
Date: September 14, 1953
Creator: O'Sullivan, William J.; Chauvin, Leo T. & Rumsey, Charles B.
Partner: UNT Libraries Government Documents Department

Exploratory tests of the behavior of several materials in a supersonic air jet at 4,000 degrees F

Description: From Summary: "Several materials have been tested in the ceramic-heated jet (laboratory model) at a Mach number of 1.96 with a stagnation temperature of approximately 4,000 degrees Fahrenheit. Test models made of molybdenum were less affected by temperature than titanium, stainless steel, and an alloy of 90 percent tungsten, 6 percent nickel, and 4 percent copper. Titanium and steel burn with highly exothermic reactions when subjected to the 4,000 degrees Fahrenheit air jet."
Date: July 29, 1957
Creator: Hopko, Russell N. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of a helicopter pressure-jet system on the Langley helicopter test tower

Description: Report presenting an investigation of a helicopter pressure-jet system. The effects of tip speed, fuel-air ratio, and pressure ratio on the propulsive characteristics of the pressure-jet system have been determined for a range of tip seeds, blade-root stagnation-pressure ratios, and fuel-air ratios. Results regarding tip-burner specific propulsive horsepower, propulsive horsepower per unit mean duct area, tip-burner specific fuel consumption, ratio of propulsive horsepower to equivalent air horsepower, effect of whirling on tip-unit thrust, effect of whirling on the tip-burner inlet pressure, effect of auxiliary fuel flow, power-off drag of tip units, and overall specific fuel consumption of pressure-jet system are provided.
Date: July 27, 1956
Creator: Makofski, Robert A. & Shivers, James P.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure distributions over the wing of the Bell X-1 research airplane (10-percent-thick wing) at subsonic and transonic speeds

Description: Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.
Date: June 29, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Flight evaluation of the lateral stability and control characteristics of the Convair YF-102 airplane

Description: Report presenting the lateral stability and control characteristics of the Convair YF-102 airplane during flights for the NACA research program. The investigation included gradually increasing sideslips, rudder-fixed aileron rolls, rudder pulses, and trim runs at two different altitudes over the test Mach number range. The lateral handling characteristics appeared satisfactory when viewed in terms of gradually increasing sideslips.
Date: January 16, 1957
Creator: Sisk, Thomas R.; Andrews, William H. & Darville, Robert W.
Partner: UNT Libraries Government Documents Department

Flight experience with a delta-wing airplane having violent lateral-longitudinal coupling in aileron rolls

Description: From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceleration limitations."
Date: October 7, 1955
Creator: Sisk, Thomas R. & Andrews, William H.
Partner: UNT Libraries Government Documents Department

Flight investigation and theoretical calculations of the fuselage deformations of a swept-wing bomber during push-pull maneuvers

Description: Report presenting the results of fuselage-deflection measurements at three stations on the fuselage of a swept-wing bomber (Boeing B-47A) during 12 push-pull maneuvers. The results are provided in the form of coefficients expressing the fuselage deflection due to normal-acceleration loads, pitching angular-acceleration loads, pitching angular-velocity loads, and the combined effect of zero-lift loads, fuselage dead weight, and landing-gear reactions. Comparisons of the theoretical and experimental results are also provided.
Date: March 29, 1957
Creator: Mayo, Alton P.
Partner: UNT Libraries Government Documents Department

Flight performance of a twin-engine supersonic ram jet from 2,300 to 67,200 feet altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

A flight study of the effects on tracking performance of changes in the lateral-oscillatory characteristics of a fighter airplane

Description: A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.
Date: October 9, 1953
Creator: McNeill, Walter E.; Drinkwater, Fred J., III & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of a solid-fuel ram jet with the internal surface of the combustor air cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. Having an internally cooled combustor averted combustor burn-out during the flight test. Results regarding acceleration, altitude, air specific impulse, and fuel specific impulse are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of NACA FR-1-B, a low-acceleration rocket-propelled vehicle for transonic flutter research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department

A flight study of requirements for satisfactory lateral oscillatory characteristics of fighter aircraft

Description: Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.
Date: July 25, 1951
Creator: Liddell, Charles J., Jr.; Creer, Brent Y. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Flight tests of a man standing on a platform supported by a teetering rotor

Description: Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date: March 24, 1954
Creator: Hill, Paul R. & Kennedy, T. L.
Partner: UNT Libraries Government Documents Department

Flight test of a radial-burning solid-fuel ram jet

Description: Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.
Date: December 10, 1952
Creator: Bartlett, Walter A., Jr. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department

Flight performance of a 2.8 KS 8100 Cajun solid-propellant rocket motor

Description: From Summary: "The performance of a 2.8 KS 8100 Cajun solid-propellant rocket motor has been determined from the free-flight test of a single-stage model which reached a velocity of 5,268 feet per second (Mach number, 4.74). Thrust data from the flight test are compared with data obtained from a ground firing test made by the manufacturer and the two are shown to be in agreement." Report presenting general drag, data, and acceleration are also provided.
Date: January 21, 1957
Creator: Lee, Dorothy B.
Partner: UNT Libraries Government Documents Department