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Wind-Tunnel Investigation of the Effects of Spoilers on the Characteristics of a Low-Drag Airfoil Equipped With a 0.25-Chord Slotted Flap

Description: Report discussing the effects of circular-arc spoilers on the section characteristics of an NACA 66,2-216 airfoil with a 0.25-chord slotted flap. Spoilers were tested on the upper surface of the airfoil, on the lower surface, and on both simultaneously. Only the simultaneous placement of spoilers was found to provide satisfactory results as a lateral control device.
Date: July 23, 1945
Creator: Holtzclaw, Ralph W.
Item Type: Refine your search to only Report
open access

Effect of the Performance of a Turbosupercharged Engine of an Exhaust-Gas-to-Air Heat Exchanger for Thermal Ice Prevention

Description: This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger. The background, results, and discussion of the investigation are described.
Date: August 23, 1945
Creator: Look, Bonne C.
Item Type: Refine your search to only Report
open access

Effect of Temperature on Beta-Ray Measurements

Description: Summary: "This report investigates photographic methods of measuring beta radiation and includes a study of temperature effects on these measurements. Experimental data are submitted to show that an increase in film temperature before and during beta irradiation causes a definite increase in density for the same dosage. Recommendations drawn from experience gained in the experimental works are offered."
Date: November 23, 1949
Creator: Stevens, A. J.
Item Type: Refine your search to only Report
open access

Procedures for the Separation of Products Resulting From Bombardment of Heavy Elements

Description: Technical report that attempts to bring together the various chemical procedures which proved most useful in studying the results of cyclotron bombardment or small scale neutron bombardments of heavy element targets. The report is limited to the elements of the "actinide", or second rare earth series, starting with thorium and including the newly discovered elements of atomic number 95 and 96. Every attempt is made to include all details necessary so this report can serve as a practical labora… more
Date: September 23, 1946
Creator: Thompson, Roy
Item Type: Refine your search to only Report
open access

An approximate method for calculating the effect of surface roughness on the drag of an airplane

Description: From Summary: "A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory."
Date: July 23, 1947
Creator: Hall, Charles F. & Fitzgerald, Fred F.
Item Type: Refine your search to only Report
open access

The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds

Description: Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
Date: April 23, 1947
Creator: Heaslet, Max A. & Nitzberg, Gerald E.
Item Type: Refine your search to only Report
open access

Investigation of the aerodynamic and icing characteristics of a recessed fuel cell vent assembly 3: NACA flush-inlet-type vent

Description: An investigation conducted in the icing research tunnel to determine aerodynamic and icing characteristics of two flush-inlet-type fuel cell vent installations. The vent tubes were mounted in two different locations in the two installations. The vents were aerodynamically investigated to obtain vent-tube static-pressure differentials and pressure surveys as a function of tunnel-air velocity and angle of attack.
Date: April 23, 1948
Creator: Ruggeri, Robert S.
Item Type: Refine your search to only Report
open access

Low-speed pressure distributions over the drooped-nose flap of a 42 degrees sweptback wing with circular-arc airfoil sections at a Reynolds number of 5.3 x 10(exp 6)

Description: Report presenting an investigation of the pressure distributions over the drooped-nose flap of a 42 degree sweptback wing with circular-arc airfoil sections and half-span trailing-edge split flaps in the 19-foot pressure tunnel. The effects of the deflection and span of the drooped-nose flap and effects of split trailing-edge flaps on the pressures over the drooped-nose flap were determined.
Date: September 23, 1948
Creator: Spooner, Stanley H. & Woods, Robert L.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at a Mach Number of 1.53 of an Airplane With a Triangular Wing

Description: Report discusses the results of an investigation into the aerodynamic characteristics of models of a tailless, pursuit-type, supersonic airplane employing a wing of triangular plan form. Measurements of lift, drag, and pitching moment, side force, drag, and yawing moment are described for several angles of attack and angles of yaw. Information about elevator and rudder behavior is also described.
Date: January 23, 1948
Creator: Scherrer, Richard & Wimbrow, William R.
Item Type: Refine your search to only Report
open access

Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio

Description: Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date: April 23, 1948
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Sweptback Wing and Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test… more
Date: July 23, 1948
Creator: Sawyer, Richard H. & Lina, Lindsay J.
Item Type: Refine your search to only Report
open access

Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock

Description: Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.
Date: July 23, 1948
Creator: Zalovcik, John A. & Luke, Ernest P.
Item Type: Refine your search to only Report
open access

Empirical mode constants for calculating frequencies of axial-flow compressor blades

Description: The vibration characteristics of a group of axial-flow compressor blades of similar geometry were investigated. Empirical-mode constants were determined for the first three bending and torsional modes. A comparison of experimentally determined frequencies of a second group of blades with frequencies computed using these mode constants showed that the computed values were correct within 10 percent. The approximate limiting ratios of depth to chord and length to chord below which these constants … more
Date: April 23, 1948
Creator: Millenson, M. B. & Wilterdink, P. I.
Item Type: Refine your search to only Report
open access

Transonic-Flutter Investigation of Wings Attached to Two Low-Acceleration Rocket-Propelled Vehicles

Description: Two low-acceleration transonic-flutter vehicles were launched and flown. The first carried two test wings, one of which fluttered at M = 0.92 at a frequency of 61.4 cycles per second. The reference flutter speed determined from two-dimensional theory for an unswept wing in incompressible flow is conservative when compared to the experimental flutter speed. The second vehicle carried two test wings, one of which failed at M = 0.71 because of low-frequency divergent oscillation. Since this failur… more
Date: November 23, 1948
Creator: Lundstrom, Reginald R.; Lauten, William T., Jr. & Angle, Ellwyn E.
Item Type: Refine your search to only Report
open access

Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Estimation of Lift and Drag of Airfoils at Near Sonic Speeds and in the Presence of Detached Shock Waves

Description: Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.
Date: February 23, 1949
Creator: Mayer, John P.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000

Description: Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date: May 23, 1947
Creator: Neely, Robert H. & Conner, D. William
Item Type: Refine your search to only Report
open access

Operating Temperatures of I-40-5 Turbojet Engine Burner Liners and the Effect of Temperature Variation on Burner-Liner Service Life

Description: Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.
Date: August 23, 1948
Creator: Wilsted, H. D.; Duffy, Robert T. & Grey, Ralph E.
Item Type: Refine your search to only Report
open access

Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Description: Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.
Date: July 23, 1948
Creator: Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Residual Stress Analysis of Overspeeded Disk With Central Hole by X-Ray Diffraction

Description: An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected nea… more
Date: July 23, 1948
Creator: Good, James N.
Item Type: Refine your search to only Report
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