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Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. It is shown that, with the antenna stabilized in space, the effect of component lags on the response is small, so that the speed of response is small, so that the speed of response can be made to approach closely that of the airframe alone.
Date: August 13, 1952
Creator: Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the… more
Date: August 13, 1952
Creator: Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Description: Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date: July 13, 1947
Creator: Alexander, Sidney R. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department
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An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 1: Characteristics of a Wing Having a Double-Wedge Airfoil Section With Maximum Thickness at 20-Percent Chord

Description: Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.
Date: November 13, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
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Longitudinal stability characteristics of the Convair YF-102 airplane determined from flight tests

Description: Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.
Date: December 13, 1956
Creator: Andrews, William H.; Sisk, Thomas R. & Darville, Robert W.
Partner: UNT Libraries Government Documents Department
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Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Description: Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow.… more
Date: August 13, 1951
Creator: Arne, Vernon L. & Nachtigall, Alfred J.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the effect of boundary-layer transition on the average heat transfer to a yawed cylinder in supersonic flow

Description: Report presenting the average heat-transfer to the forward half of a circular cylinder measured in a blowdown jet at a stream Mach number of 4.15. Most of the tests was made at a wall-to-stagnation temperature ratio of about 0.8. Report presenting pressure distributions, heat transfer and recovery temperatures, and effect of yaw on transition are provided.
Date: July 13, 1956
Creator: Beckwith, Ivan E. & Gallagher, James J.
Partner: UNT Libraries Government Documents Department
open access

Measurements of the wing and tail loads during the acceptance tests of Bell XS-1 research airplane

Description: Report presenting flight measurements obtained during acceptance tests conducted by the Bell Aircraft Corporation on the XS-1 research airplane. The primary focus was on the aerodynamic loads, handling qualities, maximum lift, and buffet boundaries of the airplane.
Date: April 13, 1948
Creator: Beeler, De E. & Mayer, John P.
Partner: UNT Libraries Government Documents Department
open access

Effect of radiant energy on vaporization and combustion of liquid fuels

Description: Report presenting an investigation of the radiative processes involved in combustion to determine the present role of radiant energy transfer in combustors. The equivalent gray-body emissivity of a hydrocarbon fuel may be increased by use of liquid or solid, soluble or nonsoluble, additives. Results regarding the experimental apparatus and methods, emission characteristics of luminous and nonluminous flames, absorptivity of fuels and of solutions of possible additives, and absorption by slurrie… more
Date: November 13, 1952
Creator: Berlad, A. L. & Hibbard, R. R.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of Four- and Six-Blade Single- and Dual-Rotating Tractor Propellers

Description: "Test of 10-foot diameter, four and six blade single-rotating and dual-rotating propellers were conducted in the NACA propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream ranged from 20 degrees to 65 degrees setting corresponds to airplane speeds greater than 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6 pe… more
Date: July 13, 1942
Creator: Biermann, David & Hartman, Edwin P.
Partner: UNT Libraries Government Documents Department
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Free-flight pressure measurements over a flare-stabilized rocket model with a modified Von Karman nose for Mach numbers up to 4.3

Description: Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.
Date: January 13, 1958
Creator: Bland, William M., Jr. & Kolenkiewicz, Ronald
Partner: UNT Libraries Government Documents Department
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Free-Flight Aerodynamic-Heating Data at Mach Numbers Up to 10.9 on a Flat-Faced Cylinder

Description: Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured an… more
Date: January 13, 1958
Creator: Bland, William M., Jr.; Swanson, Andrew G. & Kolenkiewicz, Ronald
Partner: UNT Libraries Government Documents Department
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Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

Description: "An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery fr… more
Date: July 13, 1955
Creator: Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of aerodynamically balanced trailing-edge control surfaces on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an experimental investigation of several types of aerodynamically balanced trailing-edge flaps on an aspect ratio 2 triangular wing are presented. The balancing devices tested consisted of flap overhang, paddles, rectangular and triangular horns, and trailing-edge tabs. Results regarding the lift, drag, pitching moment, hinge moment, and rolling moment are presented for a range of Mach numbers and a constant Reynolds number.
Date: February 13, 1953
Creator: Boyd, John W. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department
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Cooling of gas turbines 9: cooling effects from use of ceramic coatings on water-cooled turbine blades

Description: From Summary: "The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the traili… more
Date: October 13, 1948
Creator: Brown, W. Byron & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department
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Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane

Description: "Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data" (p. 1).
Date: February 13, 1947
Creator: Bunnell, Mort V. & Delany, Noel K.
Partner: UNT Libraries Government Documents Department
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Summary of methods for calculating dynamic lateral stability and response and for estimating aerodynamic stability derivatives

Description: "A summary of methods for making dynamic lateral stability and response calculations and for estimating the aerodynamic stability derivatives required for use in these calculations is presented. The processes of performing calculations of the time histories of lateral motions, of the period and damping of these motions, and of the lateral stability boundaries are presented as a series of simple straightforward steps. Existing methods for estimating the stability derivatives are summarized and, … more
Date: December 13, 1950
Creator: Campbell, John P. & McKinney, Marion O.
Partner: UNT Libraries Government Documents Department
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Factors Affecting Lateral Stability and Controllability

Description: The effects on dynamic lateral stability and controllability of some of the important aerodynamic and mass characteristics are discussed and methods are presented for estimating the various stability parameters to be used in the calculation of the dynamic lateral stability of airplanes with swept and low-aspect-ratio wings.
Date: May 13, 1948
Creator: Campbell, John P. & Toll, Thomas A.
Partner: UNT Libraries Government Documents Department
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Performance of wedge-type boundary layer diverters for side inlets at supersonic speeds

Description: Report presenting an experimental investigation to determine the effect of several wedge-type boundary-layer diverters on drag and inlet pressure recovery in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.5, 1.8, and 2.0. The model consisted of two rectangular ramp-type inlets mounted on the NACA RM-10 body of revolution. Results regarding variation of inlet pressure recovery and configuration drag with inlet mass-flow ratio, changes in the shock pattern off the inlet ramp, pressu… more
Date: May 13, 1954
Creator: Campbell, Robert C. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5 - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number, 2.01

Description: Memorandum presenting a supersonic wind-tunnel investigation of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with a large external store.
Date: February 13, 1956
Creator: Carlson, Harry W. & Geier, Douglas J.
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5: Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number 2.01

Description: Report presenting an investigation of store interference in the supersonic pressure tunnel at Mach number 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The interference effects measured at that Mach number were similar to those reported previously at Mach number 1.61. Results regarding store drag, store lift, store side force, store pitching moment and yawing moment, wing-fuselage drag, wing-fuselage lift, total drag, total lift, and wing-fuselage… more
Date: February 13, 1956
Creator: Carson, Harry W. & Geier, Douglas J.
Partner: UNT Libraries Government Documents Department
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Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids

Description: Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.
Date: May 13, 1954
Creator: Caves, Robert M.
Partner: UNT Libraries Government Documents Department
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Effect of Fuel-Air Ratio Concentration in Combustion Zone on Combustion Performance of a 16-Inch Ram-Jet Engine

Description: The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.
Date: April 13, 1953
Creator: Cervenka, A. J.; Bahr, D. W. & Dangle, E. E.
Partner: UNT Libraries Government Documents Department
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