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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 6 - Analysis of Effects of Inlet Pressure Losses

Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteris… more
Date: 1948
Creator: Sanders, Newell D. & Palasics, John
Item Type: Refine your search to only Report
open access

Ditching Tests of a 1/10-Scale Model of the North American XFJ-1 Airplane Ted No. NACA 314

Description: "Tests were made of a 1/10-scale dynamically similar model of the North American XFJ-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording the accelerations, and by taking motion pictures of the ditchings" (p. 1).
Date: 1948
Creator: Fisher, Lloyd J. & McBride, Ellis E.
Item Type: Refine your search to only Report
open access

Efficiency of Radial-Flow Turbine of Turbo Engineering Corporation TTT13-18 Turbosupercharger

Description: Memorandum presenting an investigation of the radial-flow turbine of the Turbo Engineering Corporation TT13-18 turbosupercharger made to evaluate the effects of inlet total pressure, inlet total temperature, and pressure ratio on the adiabatic efficiency. The results are presented by three efficiency parameters. Maximum efficiency obtained, based on total-pressure ratio and corrected for bearing friction, was 0.82 at an inlet total pressure of 50 inches of mercury absolute, an inlet total tempe… more
Date: 1948
Creator: Coulter, Earl E. & Galloway, William R.
Item Type: Refine your search to only Report
open access

Free-Spinning, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultke MX-813 (Prototype of XP-92) Airplane as Determined in the Langley 20-Foot Free-Spinning Tunnel

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel to evaluate the spin, longitudinal-trim, and tumbling characteristics of a 1/20-scale model of the Consolidated Vultee MX-813 airplane. The effects of control position were determined for the model ballasted to represent the airplane in its design gross weight loading. The model, in general, would not spin but demonstrated a tendency to trim at very high stalled angles of attack" (p. 1).
Date: 1948
Creator: Stone, Ralph W., Jr. & White, Richard P.
Item Type: Refine your search to only Report
open access

Free-Spinning-Tunnel Tests of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane

Description: "An investigation of the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics were determined, as were also the effects of extending the wing slats, of center-of-gravity movement, and-of variation in the mass distribution. The investigation also included wing-tip spin-recovery-parachute … more
Date: 1948
Creator: Daughtridge, Lee T., Jr.
Item Type: Refine your search to only Report
open access

Investigation of the Stability and Control Characteristics of a 1/10-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley Free-Flight Tunnel, TED No. NACA DE306

Description: "At the request of the Bureau of Aeronautics, Navy Department, a stability and control investigation of a 1/10-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley free-flight tunnel. Results of force end flight tests to determine the power-off stability and control characteristics of the model with slats retracted and extended are presented herein. The longitudinal and lateral stability characteristics were satisfactory for both the slats retracted and extended co… more
Date: 1948
Creator: Draper, John W. & Hewes, Donald E.
Item Type: Refine your search to only Report
open access

Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane with a Full-Span Leading-Edge Slat 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 equipped with full-span leading-edge slats has been conducted in the Langley free-flight tunnel. In this investigation it was found that the-full-span leading-edge slat gave about the same maximum lift coefficient as was obtained with the outboard single slotted flap and inboard slat. The stability and control characteristics were greatly improved e… more
Date: 1948
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
open access

Laboratory Investigation of Two Autopilots for a 4/10-Scale Drop Model of the Grumman F8F-1 Airplane, TED No. NACA 2466

Description: "Performance investigation and frequency response analyses were con- ducted en two autopilot control systems designed for use in the 0.4-scale model of the Grumman F8F-1 airplane. The first system, based on the action of a displacement gyroscope only, was investigated to find the cause of a small-amplitude pitch oscillation which had been noted in previous flight tests. The results of the investigation conducted revealed that, although the autopilot-model combination was dynamically stable, a h… more
Date: 1948
Creator: Teitelbaum, Jerome M. & Seaberg, Ernest C.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Control Characteristics of a B-29 Airplane with a Booster Incorporated in the Elevator Control System to Provide Various Stick-Force and Control-Rate Characteristics

Description: The longitudinal stability and control characteristics of a B-29 airplane have been measured with a booster incorporated in the elevator control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in pilots control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster system.
Date: 1948
Creator: Mathews, Charles W.; Talmage, Donald B. & Whitten, James B.
Item Type: Refine your search to only Report
open access

Longitudinal Stability Characteristics of a 1/40-Scale Model of a Proposed Configuration of the XF-91 Airplane Measured by the Wing-Flow Method

Description: "This report presents the results of an investigation in the transonic speed range of the longitudinal stability characteristics of a proposed configuration for the Republic XF-91 airplane. The tests covered a Mach number range of 0.55 to 1.05 and a Reynolds number range from 400,000 to 1,375,000. Lift, pitching-moment, and rolling-moment characteristics of the half model and the hinge moments on the all-moving tail were measured" (p. 1).
Date: 1948
Creator: Crane, Harold L. & Beckhardt, Arnold R.
Item Type: Refine your search to only Report
open access

Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Chance Vought XFU-1 Airplane, Ted No. NACA DE 311

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the effects of decreasing the rudder deflection, of decreasing the rudder span, and of differential rudder movements on the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane. The results indicated that decreasing the rudder span or the rudder deflections, individually or jointly, did not seriously alter the spin or recovery characteristics of the model; and r… more
Date: 1948
Creator: Berman, Theodore
Item Type: Refine your search to only Report
open access

Supplementary Investigation to Determine the Effects of Center-of-Gravity Position on the Spin, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee 7002 Airplane (Flying Mock-up of XF-92)

Description: "A supplementary wind-tunnel investigation has been conducted to determine the effect of rearward positions of the center of gravity on the spin, longitudinal-trim, and tumbling characteristics of the 1/20-scale model of the Consolidated Vultee 7002 airplane equipped with the single vertical tail. A few tests were also made with dual vertical tails added to the model. The model was ballasted to represent, the airplane in its approximate design gross weight for two center-of-gravity positions, 3… more
Date: 1948
Creator: Klinar, Walter J. & Jones, Ira P., Jr.
Item Type: Refine your search to only Report
open access

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245 deg. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectiv… more
Date: 1948
Creator: May, Ralph W., Jr.
Item Type: Refine your search to only Report
open access

A Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the MX-838 (XB-51) Airplane

Description: "At the request of the Air Material Command, U. S. Air Force, a theoretical study has been made of the dynamic lateral stability characteristics of the MX-838 (XB-51) airplane. The calculations included the determination of the neutral-oscillatory-stability boundary (R = 0), the period and time to damp to one-half amplitude of the lateral oscillation, end the time to damp to one-half amplitude for the spiral mode. Factors varied in the investigation were lift coefficient, wing incidence, wing l… more
Date: 1948?
Creator: Paulson, John W.
Item Type: Refine your search to only Report
open access

Effect of Inlet Air Distortion on the Steady-State and Surge Characteristics of an Axial-Flow Turbojet Compressor

Description: "An investigation was conducted in an altitude test chamber to determine the effects of inlet airflow distortion on the compressor steady-state and surge characteristics of a high-pressure ratio, axial-flow turbojet engine. Circumferential-type inlet flow distortions were investigated, which covered a range of distortion sector angles from 20 deg to 168 deg and distortion levels up to 22 percent. The presence of inlet airflow distortions at the compressor face resulted in a substantial increase… more
Date: January 2, 1948
Creator: Ciepluch, Carl C.
Item Type: Refine your search to only Report
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms May 13, 1947 to May 29, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities evaluated from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from May 13 to May 29, 1947 are presented.
Date: January 2, 1948
Creator: Tolefson, Harold B.
Item Type: Refine your search to only Report
open access

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Description: "An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability" (p. 1).
Date: January 9, 1948
Creator: Axelson, John A. & Crown, J. Conrad
Item Type: Refine your search to only Report
open access

Cyclic Engine Test of Cast Vitallium Turbine Buckets 2

Description: Memorandum presenting an investigation conducted to provide data that may be used to correlate the engine service performance of cast Vitallium turbine buckets with metallurgical properties. Data were obtained from four turbine wheels of Timken alloy with cast Vitallium buckets. Examination of 12 broken buckets indicated that 8 of the failures were probably caused by fatigue and 4 by impact with pieces of other broken buckets.
Date: January 12, 1948
Creator: Farmer, J. Elmo; Deutsch, George C. & Sikora, Paul F.
Item Type: Refine your search to only Report
open access

High-Speed Aerodynamic Characteristics of a Model Tail Plane with Modified NACA 65-010 Sections and 0 Degree and 45 Degrees Sweepback

Description: Memorandum presenting wind-tunnel tests that have been made to determine the aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and a tapered plan form. Results were obtained with the model tail plane unswept and swept back. The data show the lift, drag, pitching-moment, and hinge-moment coefficient variation with angle of attack and flap deflection at various Mach numbers.
Date: January 12, 1948
Creator: Anderson, Joseph L. & Martin, Andrew
Item Type: Refine your search to only Report
open access

Flight Characteristics at Low Speed of Delta-Wing Models

Description: Report presenting an investigation to obtain a survey of the flying characteristics at low speeds of models with low-aspect-ratio delta wings. Four models with triangular plan-form sweptback wings and five models with the tips cut off to give taper ratios were tested. Results regarding the stability and control characteristics of each of the models is provided.
Date: January 13, 1948
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
Item Type: Refine your search to only Report
open access

Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet

Description: Memorandum presenting a flight investigation conducted on a 20-inch-diameter steady-flow ramjet at a range of altitudes and free-stream Mach numbers. Results regarding the variation of combustion efficiency with fuel-air ratio and pressure altitude, effects of combustion-chamber-inlet velocity, and altitude on the operating range of fuel-air ratio are provided. The ramjet unit operated smoothly over the entire range of velocities and altitudes with the exception of occasional rough operation at… more
Date: January 14, 1948
Creator: Disher, John H.
Item Type: Refine your search to only Report
open access

Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control

Description: Memorandum presenting an analytical method developed that gives two independent means of obtaining the total-temperature ratio across a ram jet or across a turbojet tail-pipe burner without direct measurement of the final gas temperature. Experimental verification of the analysis has been obtained with a 20-inch ram jet over a wide range of operating conditions.
Date: January 14, 1948
Creator: Perchonok, Eugene; Sterbentz, William H. & Moore, Stanley H.
Item Type: Refine your search to only Report
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