National Advisory Committee for Aeronautics (NACA) - 48 Matching Results

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A Further Investigation of the Meteorological Conditions Conducive to Aircraft Icing

Description: Report presenting meteorological data from flight observations in icing conditions during the winter of 1946-47. Data on liquid water content, temperature, and mean-effective drop diameter are consistent with values previously proposed for maximum icing conditions. Results regarding the icing conditions in altostratus clouds, reexamination of previously proposed design conditions, relation between maximum liquid water content and temperature in layer clouds, typical icing conditions, maximum dr… more
Date: October 1947
Creator: Lewis, William; Kline, Dwight B. & Steinmetz, Charles P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalized Performance Comparison of Large Conventional, Tail Boom, and Tailless Airplanes

Description: Report presenting an investigation to determine the performance of large tailless and conventional airplanes. The primary conclusion drawn fro the testing is that large all-wing tailless airplanes may have better performance characteristics than their equivalent tail-boom airplanes for certain types of missions. Results regarding a general performance comparison, performance variations with structural weight, landing speed, and take-off distance, and performance comparison based on arbitrary de… more
Date: October 1947
Creator: Ankenbruck, Herman O. & McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impact Theory for Seaplane Landings

Description: Note presenting an analysis of a step landing of a seaplane on smooth water by solving Newton's differential equation of motion. Formulas are developed for the maximum acceleration, the maximum draft, and the draft at the instant of maximum acceleration.
Date: October 1947
Creator: Benscoter, Stanley U.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of High-Lift and Stall-Control Devices on a NACA 64-Series 42 Degree Sweptback Wing With and Without Fuselage

Description: Report presenting an investigation of a 42 degree sweptback wing of aspect ratio 4, taper ratio 0.625, and NACA 64-series airfoil sections to study several proposed devices for increasing the maximum lift coefficient and improving the longitudinal stability characteristics of sweptback wings at the stall. Some of the devices tested included leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper-surface fences. The results regarding the c… more
Date: October 14, 1947
Creator: Graham, Robert R. & Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of NACA 65(sub 112) A111 (approx.) airfoil with 0.35-chord slotted flap at Reynolds numbers up to 25 million

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel and low-turbulence pressure tunnel to determine the highest maximum lift configurations of a slotted flap on an NACA 65(sub 112)A111 (approx.) airfoil section. The scale effects on aerodynamic characteristics were determined for a range of Reynolds numbers. Results regarding flap configurations, lift characteristics, pitching-moment characteristics, drag characteristics, and effects of leading-edge roughness are pro… more
Date: October 1947
Creator: Racisz, Stanley F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel Part 5 - Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage TED No. NACA DE308, Part V, Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage, TED No. NACA DE308

Description: "Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The wing-alone tests and the effect of the various vertical-fin modifications, speed-brake modifications, and fuselage modifications on the aerodynamic characteristics in pitch and yaw are presented in the present paper with a limited analysis of the results. Also i… more
Date: October 10, 1947
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Operating Properties of the Leakage Current Anemometer

Description: "Freedom from inertia, erosion of electrodes, and reaction make the leakage current particularly appropriate for the measurement of flow velocities in gases. Apparatus previously described has now been improved by reducing the size of the electrodes by one -thousandth, as is necessary aerodynamically, and by increasing the magnitude of the current from 1000 to 10,000 times; the latter result was obtained.by use of mercury high-pressure lamps set up at the one focal point of an ellipsoidal refle… more
Date: October 1947
Creator: Fucks, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Turbine of Mark 25 Torpedo Power Plant with Five Nozzle Designs

Description: "Efficiency investigations were made on the two-stage turbine from a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. A method was developed for measuring the change in turbine clearances with changed operating conditions. The turbine was found to be most efficient with a cast nozzle having a sharp-edged inlet to the nine nozzle p… more
Date: October 8, 1947
Creator: Hoyt, Jack W. & Kottas, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lateral stability and control characteristics of an airplane model having 42.8 degree sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces

Description: Report presenting testing in the 300 mph 7- by 10-foot tunnel of an airplane model with a 42.8 degree sweptback wing with an aspect ratio 4.00, taper ratio 0.50, a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine the low-speed lateral stability and control characteristics. Some changes made to improve the aerodynamic characteristics included lowering the wing, incorporating a smaller-fineness-ratio fuselage, and increasing the vertical tail size. Res… more
Date: October 17, 1947
Creator: Goodson, Kenneth W. & Comisarow, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Limits of Precision in the Determination of Lattice Parameters and Stresses by the Debye-Scherrer Method

Description: Note an investigation regarding the limits of precision in the determination of lattice parameters. Experiments were performed with copper radiation on zinc samples. Even when the crystal-grain orientation is perfectly uniform, the recording of the intensity distribution will entail errors.
Date: October 1947
Creator: Ekstein, Hans & Siegel, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics of an Airplane Model Having a 42.8 Degree Sweptback Circular-Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback Tail Surfaces

Description: Report presenting testing of an airplane model with a 42.8 degree sweptback wing with an aspect ratio of 4.00, taper ratio of 0.50, and a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine its low-speed longitudinal stability and control characteristics. Other variables investigated include the vertical-wing location, fuselage size, horizontal-tail location, and stall-control vanes on the wing.
Date: October 17, 1947
Creator: Weil, Joseph; Comisarow, Paul & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings

Description: Report presenting an investigation at low speed to determine static stability and damping-in-roll characteristics of a number of low-aspect-ratio wings, including swept wings of approximately triangular plan form, in the free-flight and 15-foot free-spinning tunnels. Static longitudinal stability, directional stability, effective dihedral, and damping in roll are provided.
Date: October 1947
Creator: Tosti, Louis P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of Atmospheric Turbulence on Seattle-Alaska Airways

Description: "For about the past year, American Airlines has been engaged in obtaining data on various uses of airborne radar under routine operating conditions. This work is under contract to the Navy Department, Bureau of Ships, and includes the investigation of radar as a navigational aid and terrain collision warning device and its use in icing and turbulence detection. In view of the work of the National Advisory Committee for Aeronautics on atmospheric turbulence, the NACA was requested to participate… more
Date: October 21, 1947
Creator: Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Application of the Energy Method to Stability Problems

Description: "Since stability problems have come into the field of vision of engineers, energy methods have proved to be one of the most powerful aids in mastering them. For finding the especially interesting critical loads special procedures have evolved that depart somewhat from those customary in the usual elasticity theory. A clarification of the connections seemed desirable,especially with regard to the post-critical region, for the treatment of which these special methods are not suited as they are" (… more
Date: October 1947
Creator: Marguerre, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Performance of a Composite Engine Consisting of a Reciprocating Spark-Ignition Engine, a Blow-Down Turbine, and a Steady-Flow Turbine

Description: Report presenting an analysis of the performance of a composite engine consisting of a reciprocating spark-ignition engine, two superchargers, a blowdown turbine, and a steady-flow turbine. The performance of the configuration was analyzed in order to determine the suitability and cost of design compromises when the size of turbines and superchargers and all gear ratios are assumed fixed. Results regarding the variable-component system, fixed-component system, and auxiliary-propeller system are… more
Date: October 1947
Creator: Turner, L. Richard & Noyes, Robert N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Ram-Jet Engine for Fighters

Description: Simple and accurate calculations are made of the flow process in a continuous compressorless Lorin jet-propulsion unit. Experimental confirmation is given from towing tests on an airplane at flying speeds up to 200 miles per second. An analysis is made of the performance of a fighter-type airplane designed for utilization of this propulsion system.
Date: October 1947
Creator: Sänger, E. & Bredt, I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Tests and Calculations Pertaining to the Dive Path and to Wing and Tail Loads in the Accident to Eastern Airlines C54B Airplane, NC-88814, Near Bainbridge, Maryland, May 30, 1947

Description: "Several dive paths were calculated for a C54 airplane starting from level flight at an altitude of 4000 feet and from an initial indicated airspeed of 200 miles per hour. The results show that, within the limits of the possible paths permitted by the evidence of the crash at Bainbridge, the speed of impact would be about 370 miles per hour and the time to crash would be between 12 1/2 and 15 1/2 seconds. Tail load calculations indicate that, with moderate negative acceleration of the airplane,… more
Date: October 22, 1947
Creator: Rhode, Richard V.; Stokke, Allen R. & Rogin, Leo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Spot Welding of Dissimilar Aluminum Alloys in the 0.040-Inch Thickness

Description: Note presenting an investigation of the spot welding of eight dissimilar alloy combinations in 0.40-inch thickness as part of a program on aircraft spot-welding. The results indicate that in many instances, the chemical treatment of dissimilar alloys prior to spot welding is a less difficult problem than the treatment of some similar alloy combinations. They also indicated that all of the combinations can be spot-welded with little difficulty.
Date: October 1947
Creator: Hess, W. F.; Wyant, R. A. & Winsor, F. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability of Plates and Shells Beyond the Proportional Limit

Description: In the present paper is examined the method of investigating the stability of plates and shells beyond the elastic limit, that proceeds from the generalization of the Hencky-Mises theory of elastico-plastic deformations given in the works of Smirnov-Alyayev, Schmidt, and in our papers.
Date: October 1947
Creator: Ilyushin, A. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift

Description: Note presenting equations derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Results regarding section wave drag and wing wave drag are provided.
Date: October 1947
Creator: Margolis, Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift

Description: "On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms" (p. 1).
Date: October 6, 1947
Creator: Margolis, Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Data on Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations

Description: "A total of 197 hours of time histories of airspeed and altitude have been obtained on Lockheed Constellation airplanes flying between New York, N.Y. and San Francisco, Calif. during May 1946 and June 1946. Data for 130 hours were previously analyzed to determine the probability of attaining excessive airspeeds and Mach numbers and the results have been published. After the publication, data for additional 67 hours became available" (p. 1).
Date: October 10, 1947
Creator: Steiner, Roy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supplementary Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the McDonnell XB-85 Airplane Equipped with a Conventional-Tail Arrangement

Description: "Spin tests have been conducted in the Langley free-spinning tunnel on a 1/16-scale model of the McDonnell XP-85 airplane with the normal X-tail replaced with a short-coupled conventional tail arrangement. The effect of the conventional tail arrangement and the effects of various modifications upon the spin and recovery characteristics of the model were determined. The results of the tests indicated that installation of the conventional tail arrangement will not provide satisfactory recoveries … more
Date: October 13, 1947
Creator: Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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