National Advisory Committee for Aeronautics (NACA) - 184 Matching Results

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A Method for Predicting the Stability in Roll of Automatically Controlled Aircraft Based on the Experimental Determination of the Characteristics of an Automatic Pilot

Description: Report presenting a method for predicting the stability of automatically controlled aircraft by comparing the calculated frequency-response curves for the aircraft and experimentally determined frequency-response curves for the automatic pilot. The method is applicable only to stabilization in roll. It can be used to establish the specifications of performance required for the automatic control device for pilotless aircraft designed as missiles.
Date: January 17, 1947
Creator: Jones, Robert T. & Sternfield, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Compressor XJ-41-V Turbojet Engine 1 - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Description: From Summary: "At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compress… more
Date: January 17, 1947
Creator: Ginsburg, Ambrose & Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

Description: From Summary: "The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surf… more
Date: February 17, 1947
Creator: Hillendahl, Wesley H. & George, Ralph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Description: Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in… more
Date: February 17, 1947
Creator: Havens, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of shock diffusers at Mach number 1.85 1: projecting single-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine design conditions for optimum performance of shock diffusers at Mach number 1.85 with a series of projecting single-shock cones with varying angles. Each cone was tested with a curved and a straight diffuser-inlet section. The effect of angle of attack was investigated for several configurations.
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees. more
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of Xj-41-v Turbojet Engine, 3, Compressor Static-Pressure Rise at Equivalent Compressor Speeds of 5000, 7000, 8000, and 9000 RPM

Description: "At the request of the Air Materiel Command, Army Air Forces, an investigation is being conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The static-pressure variation in the direction of flow through the compressor was presented in reference 1 for an equivalent speed of 8000 rpm. An analysis of these pressure indicated that the maximum-flow limitation of the compressor was caused by separation, which reduced the e… more
Date: July 17, 1947
Creator: Creagh, John W. R. & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349

Description: "Spin tests of a 1/16-scale model of the Chance Vought XF5U-1 airplane have been performed in the Langley 20-foot free-spinning tunnel. The effect of control position and movement upon the erect and inverted spin and recovery characteristics as well as the effects of propellers, of stability flaps, and of various revisions to the design configuration have been determined for the normal fighter loading. The investigation also included spin recovery parachute, tumbling, and pilot-escape tests" (p… more
Date: October 17, 1947
Creator: White, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
open access

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
open access

Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

Description: "An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impos… more
Date: November 17, 1947
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XP-85 Airplane While Attached to the Trapeze

Description: "At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was … more
Date: November 17, 1947
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Rolling Effectiveness of a Wing-Spoiler Arrangement at High Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting an investigation of the rolling effectiveness of a wing-spoiler arrangement using a rocket-propelled test vehicle in free flight. The configuration investigated in the report is likely not optimum and indicates a need for further exploration.
Date: May 17, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the North American XP-86 Airplane

Description: "A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined" (p. 1).
Date: May 17, 1948
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of 24-Inch Supersonic Axial-Flow Compressor in Air 1: Performance of Compressor Rotor at Design Tip Speed of 1600 Feet Per Second

Description: Memorandum presenting an investigation of an axial-flow compressor rotor operating with supersonic velocities relative to the blade rows in order to determine the performance characteristics in air and to confirm the performance obtained in Freon-12 at another laboratory. Results regarding the weight flow, work of compression, pressure ratio and adiabatic efficiency, and entry of shock are provided.
Date: May 17, 1948
Creator: Ritter, William K. & Johnsen, Irving A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Qualitative Measurements of Relative Flap Effectiveness at Transonic Speeds on a Series of Five Thin Airfoils With 25-Percent-Chord Flaps and Various Amounts of Sweepback

Description: Report presenting testing on a series of five flat plate models of aspect ratio 2.0 with 25-percent-mean-aerodynamic-chord flaps at a range of Mach numbers in order to investigate the effect of sweepback on flap effectiveness.
Date: May 17, 1948
Creator: Crane, Harold L. & McLaughlin, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Control during starting of gas-turbine engines

Description: Report presenting an investigation of the variables pertinent to the control of gas temperatures of gas-turbine engines during starting conducted by obtaining time records of the variables involved during actual starting conditions. Poor control of gas temperatures during starting was found to be caused by an accumulation of fuel in the engine before ignition and excessive fuel-flow rates at the time of ignition.
Date: June 17, 1948
Creator: Koenig, Robert J. & Dandois, Marcel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theoretical lateral-stability analysis of XC-120 airplane

Description: "A theoretical lateral-stability analysis of the XC-120 airplane, equipped with a detachable fuselage, was made to determine the effect on the lateral stability of the high angle of wing incidence for which the airplane was designed. The results of the investigation indicated that the lateral stability of the airplane is satisfactory with or without the detachable fuselage installed" (p. 1).
Date: September 17, 1948
Creator: Sternfield, Leonard & Gates, Ordway B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Description: Report presenting control requirements and parameters for a ram jet with a variable-area exhaust nozzle, which have been analyzed from calculated performance charts covering flight Mach numbers from 0.6 to 3.0 and altitudes from sea level to 30,000 feet. Requirements for maximum efficiency, safe and stable operation, maximum range of thrust at a given flight Mach number, and control of fuel flow are discussed and control parameters are selected.
Date: November 17, 1948
Creator: Boksenbom, Aaron S. & Novik, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds

Description: From Summary: "Results are presented of an experimental investigation of the characteristics of NACA submerged inlets on a model of a fighter airplane for Mach numbers from 0.30 to 0.875. The effects on the ram-recovery ratio at the inlets of Mach number, angle of attack, boundary-layer thickness on the fuselage, inlet location, and boundary-layer deflectors are shown. The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as … more
Date: November 17, 1948
Creator: Hall, Charles F. & Frank, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of horizontal tails 3: unswept and 35 degrees swept-back plan forms of aspect ratio 6

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. Test results are provided for models with and without standard roughness on their leading edges and with sealed and unsealed radius-nose elevators. Results regarding effectiveness and hinge-moment parameters, static longitudinal stability, effect of standard roughness, and effect of removing the elevator nose … more
Date: December 17, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92

Description: Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone.
Date: February 17, 1949
Creator: Brown, Clinton E. & Heinke, Harry S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calibration Tests of a German Log Rodmeter

Description: A German log rodmeter of the pitot static type was calibrated in Langley tank no. 1 at speeds up to 34 knots and angles of yaw from 0 deg to plus or minus 10 3/4 degrees. The dynamic head approximated the theoretical head at 0 degrees yaw but decreased as the yaw was increased. The static head was negative and in general became more negative with increasing speed and yaw. Cavitation occurred at speeds above 31 knots at 0 deg yaw and 21 knots at 10 3/4 deg yaw.
Date: March 17, 1949
Creator: Mottard, Elmo J. & Stillman, Everette R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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