National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

Search Results

prev Results: 81 - 104 next
open access

Force and pressure measurements at transonic speeds for several bodies having elliptical cross sections

Description: Report presenting the measured force characteristics and surface-pressure distributions at a range of angles of attack for a series of bodies with elliptical cross sections. Results regarding pressure data and force data are provided.
Date: September 1958
Creator: McDevitt, John B. & Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation to Determine the Drag of Flat- and Vee- Windshield Canopies on a Parabolic Fuselage With and Without Transonic Indentation Between Mach Numbers of 0.75 and 1.35

Description: Note presenting a free-flight investigation between Mach numbers of 0.75 and 1.35 to determine the effects on model total drag and pressure drag of (a) canopy location, (b) canopy windshield shape, (c) canopy fineness ratio, and (d) transonic-area-rule indentation.
Date: September 1958
Creator: Kouyoumjian, Walter L. & Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Friction and wear with reactive gases at temperatures up to 1200 degrees F

Description: Report presenting friction and wear experiments conducted to explore the effects of high temperature, varied chlorine content, sulfur catalysis, and preformation of sulfide films on boundary lubrication with reactive gases. Results regarding sulfur hexafluoride, dichlorodifluoromethane, chlorotrifluoromethane, chlorotrifluorometahne plus sulfur hexafluoride, and dichlorodifluoromethane plus sulfur hexafluoride are provided.
Date: September 1958
Creator: Allen, Gordon P.; Buckley, Donald H. & Johnson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Graphs of reduced variables for computing histories of vaporizing fuel drops, and drop histories under pressure

Description: Report presenting an investigation with two purposes: to obtain a simplified calculation technique for replacing complicated automatic computer calculations and to obtain experimental data for single droplets vaporizing at pressures greater than 1 atmosphere and to check the histories against experimental data.
Date: September 1958
Creator: Borman, G. L.; El Wakil, M. M.; Uyehara, O. A. & Myers, P. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer and Thermal Stresses in Sandwich Panels

Description: Note presenting calculated maximum temperature differences between faces and calculated thermal stresses for sandwich panels with a prescribed linear rate of temperature rise and at one face and with the other face insulated. Maximum temperature differences between top and bottom faces are considerably less when both radiation and conduction are considered than when radiation is neglected. Results regarding dimensionless analysis, correlation of theory and experiment, and thermal stresses are p… more
Date: September 1958
Creator: Swann, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Impact Loads on 30 Degree and 60 Degree V-Step Plan-Form Models With and Without Dead Rise

Description: Note presenting an investigation of the hydrodynamic impact loads of 30 and 60 degree included-angle V-step models in the impact basin. The investigation consisted of a series of fixed-trim impacts in smooth water with a dead-rise model with a round keel and chine flare and a beam-loading coefficient of 3.6. The data are presented in a table, and typical time histories and variations of maximum impact lift and maximum drag with trim and flight-path angle are included.
Date: September 1958
Creator: Edge, Philip M., Jr. & Mason, Jean P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hypersonic Viscous Flow Over Slender Cones

Description: Note presenting viscous self-induced pressures on 3 degree semivertex angle cones measured over a free-stream Mach number range and viscous-interaction parameter range. Results regarding the experiment, comparison between theory and experiment, and hole-size effect are provided.
Date: September 1958
Creator: Talbot, Lawrence; Koga, Toyoki & Sherman, Pauline M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of boiling burnout and flow stability for water flowing in tubes

Description: Report presenting measurements of boiling-burnout heat-transfer rates with water flowing vertically upward in electrically heated tubes. Flow stability in the test section during burnout was affected by the amount of pressure drop across a throttling valve located upstream. A compressible volume introduced in the flow system between the throttling valve and the test section resulting in unsteady flow during burnout.
Date: September 1958
Creator: Lowdermilk, Warren H.; Lanzo, Chester D. & Siegel, Byron L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Minimum Drag and Maximum Lift-Drag Ratios of Several Wing-Body Combinations Including a Cambered Triangular Wing at Low Reynolds Numbers and at Supersonic Speeds

Description: Theoretical and experimental data for wing-body combinations with wings of triangular, arrow, and diamond plan form are presented for Mach numbers of 1.62, 1.93, and 2.41 and a Reynolds number range of 1.4 x 10 to the 6th power to 0.7 x 10 to the 6th power. Included are two each of triangular and arrow plan-form wings cambered for approximately uniform load at m = 1.62 and lift coefficients of 0.08 and 0.20. Liquid-film studies of the flow over the various configurations are also presented.
Date: September 1958
Creator: Brown, Clinton E. & Hargrave, L. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of some phenomena relating to aural detection of airplanes

Description: Report presenting an investigation to determine the effect of modifications made in the propulsion system of a single-engine airplane to substantially reduce its external noise, and, thereby, to evaluate the significance of the external noise level of an airplane with regard to the problem of its detection by ground observers.
Date: September 1958
Creator: Hubbard, Harvey H. & Maglieri, Domenic J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of supersonic turbulent boundary layers on slender bodies of revolution in free flight by use of a Mach-Zehnder interferometer and shadowgraphs

Description: Report presenting a study of slender bodies of revolution in free flight at Mach numbers 3.2 and 3.6, which were photographed and analyzed to obtain the turbulent-boundary-layer density distributions for the case of a body surface that is cold compared to recovery temperature. Results regarding density profiles, density distributions, comparison with the Crocco equation, calculation of the heat-transfer rate, and observations of the turbulent-boundary-layer image structure from shadowgraphs, an… more
Date: September 1958
Creator: Seiff, Alvin & Short, Barbara J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of Atmospheric Corrosion on the Fatigue Life of Aluminum Alloys

Description: "Fatigue tests were conducted on 100 vibrating cantilever sheet specimens by applying 4,000 cycles of load in a 10-minute period each working day while the specimens were subjected to atmospheric conditions over a period of several months. Specimens of 2024-T3 and 7075-T6 aluminum alloys in both the bare and clad forms were tested. For comparison, 96 specimens were tested indoors" (p. 1).
Date: September 1958
Creator: Leybold, Herbert A.; Hardrath, Herbert F. & Moore, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lag in Pressure Systems at Extremely Low Pressures

Description: "A theoretical formula for determining time lags in pressure-measuring systems at all pressures, including extremely low pressures where molecular flow occurs, is derived and shown to be accurate to within 10 percent for pressure down to approximately 0.2 millimeter of mercury (0.556 lb/sq ft) for nearly linear pressure changes" (p. 1).
Date: September 1958
Creator: Davis, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Large-scale wind-tunnel tests of an airplane model with an unswept, aspect-ratio-10 wing, two propellers, and area-suction flaps

Description: Report presenting an investigation to determine the effects of a propeller slipstream on the lift obtainable and flow requirements for suction applied to the porous area of a trailing-edge flap on a model of a twin-engine airplane with a high-aspect-ratio, thick, straight wing. Results regarding aerodynamic characteristics, flap suction requirements, aileron suction requirements, and comparison with the Arado system are provided.
Date: September 1958
Creator: Weiberg, James A.; Griffin, Roy N., Jr. & Florman, George L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift and profile-drag characteristics of an NACA 0012 airfoil section as derived from measured helicopter-rotor hovering performance

Description: Report presenting synthesized rotor-blade section lift and profile-drag characteristics for an NACA 0012 airfoil section as a function of angle of attack and Mach number for use in calculations of helicopter-rotor hovering performance are presented. At low tip Mach numbers, the synthesized data have higher maximum lift and lower profile drag at maximum lift than the equivalent two-dimensional airfoil data. Results regarding synthesized blade-section characteristics, rotor hovering characteristi… more
Date: September 1958
Creator: Carpenter, Paul J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lightning Hazards to Aircraft Fuel Tanks

Description: Note presenting an investigation of the hazards of lightning strikes to aircraft fuel tanks in a specially constructed facility meant to duplicate natural lightning discharges on aircraft. Explosion studies were made in an environmental explosion chamber using small fuel tanks under various simulated flight conditions. The results showed that there is a primary hazard whenever there is direct puncture of the fuel-tank wall, whereas the ignition of fuel by hot spots on tank walls due to lightnin… more
Date: September 1958
Creator: Robb, J. D.; Hill, E. L.; Newman, M. M. & Stahmann, J. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low tire friction and cornering forces on a wet surface

Description: Report presenting an investigation to study typical tire behavior on wet runways, to determine the mechanisms by which water on runways reduced tire forces, and to determine the extent of this tire-force reduction. Under certain conditions of tire pressure, velocity, and water depth, the smooth-treaded tires stop rotating and begin to plane even without the application of brakes. Results regarding the smooth-tire friction coefficients, friction coefficients of the diamond-treaded tire, effect o… more
Date: September 1958
Creator: Harrin, Eziaslav N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Mach 4 rocket-powered supersonic tunnel using ammonia-oxygen as working fluid

Description: From Summary: "A rocket-powered supersonic tunnel has been constructed to simulate the high heating rates encountered in hypersonic flow. A gas temperature of 4500 degrees Rankine at Mach 4 has been produced in the 15-inch test section of the tunnel. The calibration pressure data indicate reproducibility of test conditions in this facility. Physical, transport, and one-dimensional aerodynamic data from combustion products of ammonia and oxygen are included."
Date: September 1958
Creator: Graham, Robert W.; Guentert, Eleanor Costilow & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Mass Transfer Cooling Near the Stagnation Point

Description: "A simplified analysis is made of mass transfer cooling - that is, injection of a foreign gas - near the stagnation point for two-dimensional and axisymmetric bodies. The reduction in heat transfer is given in terms of the properties of the coolant gas and it is shown that the heat transfer may be reduced considerably by the introduction of a gas having appropriate thermal and diffusive properties. The mechanism by which heat transfer is reduced is discussed" (p. 1).
Date: September 1958
Creator: Roberts, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord

Description: Report presenting some experimental measurements of aerodynamic forces and moments on a simple T-tail configuration oscillating in yaw about an axis through the midchord of the vertical fin. Coefficients regarding the rolling moment of the horizontal stabilizer, rolling moment, yawing moment, and side force of the tail are provided.
Date: September 1958
Creator: Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of ground-reaction forces and vertical center-of-gravity accelerations of a bomber airplane taxiing over obstacles

Description: Report presenting an investigation made on an unswept-wing four-engine bomber airplane to determine the vertical and drag ground-reaction forces imposed on the landing gear when taxiing over obstacles of various sizes. Results are presented of the effects of ground speed and the widths and heights of the obstacles on the vertical and drag forces, vertical acceleration at the center of gravity of the airplane, on shock-strut displacement, and on response of the upper mass of the airplane structu… more
Date: September 1958
Creator: McKay, James M.; Sawyer, Richard H. & Hall, Albert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the Motions of a Large Swept-Wing Airplane in Rough Air

Description: Note presenting flight test measurements of the angular and linear motions of a large swept-wing airplane in rough air for a range of altitudes. The measurements are summarized in the form of power spectra, root-mean-square values, and probability distributions. A procedure is given for extrapolating the measurements of the probability distributions and the power spectra to other turbulence conditions.
Date: September 1958
Creator: Rhyne, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for Determining the Need to Rework or Replace Compressor Rotor Blades Damaged by Foreign Objects

Description: Note presenting a method for deciding whether jet-engine compressor blades that have been nicked in service are safe from fatigue failure with continued engine operation. The method involves determining the vibratory stress distribution of the blades with damage inflicted in the laboratory. The method is judged to be a realistic criterion on inspecting damaged blades.
Date: September 1958
Creator: Kaufman, Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Natural convection inside a flat rotating container

Description: Report presenting an exploration of Froude number, which is found to be the parameter that determines the effect of body rotations on internal natural convection flows. Explicit forms of Froude number are determined for the cases of predominant rotation and predominant axial force. Results indicated that in a heated cylindrical container no significant convective effects are generated by rotations alone.
Date: September 1958
Creator: Ostrach, Simon & Braun, Willis H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen