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

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Drag of C-class airship hulls of various fineness ratios

Description: From Summary: "This report presents the results of wind-tunnel tests on eight C-class airship hulls with various fineness ratios, conducted in the Navy Aerodynamic Laboratory, Washington. The purpose of the tests was to determine the variation of resistance with fineness ratio, and also to find the pressure and friction elements of the total drag for the model having the least shape coefficient. Seven C-class airship hulls with fineness ratios of 1.0, 1.5, 2.0, 3.0, 6.0, 8.0, and 10.0 were made… more
Date: 1928
Creator: Zahm, A. F.; Smith, R. H. & Louden, F. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Forces on elliptic cylinders in uniform air stream

Description: From Summary: "This report presents the results of wind tunnel tests on four elliptic cylinders with various fineness ratios, conducted in the Navy Aerodynamic Laboratory, Washington. The object of the tests was to investigate the characteristics of sections suitable for streamline wire which normally has an elliptic section with a fineness ratio of 4.0; also to learn whether a reduction in fineness ratio would result in improvement; also to determine the pressure distribution on the model of f… more
Date: 1929
Creator: Zahm, A. F.; Smith, R. H. & Louden, F. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Effect of Some Airplane Handling Techniques on the Ground-Run Distance in Landing on Slippery Runways

Description: Note presenting some calculations made on the basis of simplifying assumptions to determine the effect on the ground-run distance of maintaining a nose-high attitude instead of a three-point attitude in landings of several types of jet airplanes on slippery runways. The airplanes considered were a swept-wing transport and unswept-, swept-, and delta-wing fighters. Results regarding the effect of airplane attitude and effect of flap retraction are provided.
Date: July 1957
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Boundary-Layer and Profile-Drag Characteristics of Smooth Wing Sections of a P-47D Airplane

Description: "In Mach range of 0.25 - 0.69, boundary-layer measurements were made on upper wing surface at 25% semi-span, pressure-distribution measurements made on upper surface at 63% semi-span, and wake surveys made at 63% semi-span. The minimum profile-drag coefficient of 0.0062 was indicated for smooth section at 63% semi-span. Critical mach number was exceeded by 0.04, but no compressibility shocks appeared. In slipstream, boundary layer transition occurred as far back as 20% chord on upper surface at… more
Date: October 1945
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Boundary-Layer and Profile-Drag Characteristics of Smooth Wing Sections of a P-47D Airplane

Description: Report presenting a flight investigation made of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane. Measurements were made at three stations on the wing: boundary-layer measurements, pressure-distribution measurements, and wake surveys. The results indicated that a minimum profile-drag coefficient of 0.0062 for the smooth section at 63 percent semispan was obtained.
Date: October 1945
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight

Description: "The results of flight investigations of the profile drag of several carefully finished conventional and low-drag airfoils are presented. The results indicated that in all cases lower profile-drag coefficients were obtained with the low-drag than with the conventional airfoils over the range of lift coefficient tested and that, for comparable conditions of lift coefficient and Reynolds number, the low-drag airfoils may have profile-drag coefficients which are at least 27 percent lower than the … more
Date: May 1944
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight

Description: Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically.
Date: May 1944
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Profile-Drag Investigation in Flight on an Experimental Fighter-Type Airplane the North American XP-51

Description: Report discussing the results of an investigation of the North American XP-51 and its low-drag airfoils. Several surface conditions were tested and the profile-drag coefficients were determined. The surface that was smoothened and faired by filling and sanding had the lowest profile-drag coefficient.
Date: November 1942
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A radar method of calibrating airspeed installations on airplanes in maneuvers at high altitudes and at transonic and supersonic speeds

Description: A method of calibrating the static-pressure source of a pitot static airspeed installation on an airplane in level flight, dives, and other maneuvers at high altitude and at transonic and supersonic speeds is described. The method principally involves the use of radar-phototheodolite tracking equipment. The various sources of error in the method are discussed and sample calibrations are included.
Date: August 31, 1949
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Summary of stall-warning devices

Description: From Summary: "The principles involved in the operation of several types of stall-warning devices are described and conditions under which difficulty may be experienced are pointed out. In the discussion, stall-warning devices are grouped as special stall-sensing devices and angle-of-attack-sensing devices. Methods of transmitting the warning to the pilot are also discussed. Some specific examples of stall-warning devices are illustrated and described."
Date: May 1952
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing

Description: Report discusses an investigation into static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The results obtained from the three types of measuring devices and a comparison to theoretical calculations are presented.
Date: November 1944
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Speeds of Profile Drag of Wing of a P-47d Airplane Having Production Surfaces Covered With Camouflage Paint

Description: Report presenting a flight investigation made at high speeds to determine the profile drag of a P-47D airplane wing with production surfaces covered with camouflage paint. The results indicated that a minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach numbers less than 0.67.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back 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 of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.
Date: March 28, 1947
Creator: Zalovcik, John A. & Sawyer, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Boundary-Layer Transition and Profile Drag of an Experimental Low-Drag Wing Installed on a Figher-Type Airplane

Description: Report presenting a boundary-layer-transition and profile-drag investigation conducted on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed. Results regarding the right wing section outside the slipstream and left wing section in the propeller slipstream a… more
Date: April 1945
Creator: Zalovcik, John A. & Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Flight Investigation of the Effect of Surface Roughness on Wing Profile Drag With Transition Fixed

Description: Report presenting a flight investigation made on a wing section of a P-47D airplane to determine the effect of roughness on wing profile drag with transition fixed far forward. Surveys of the wake were made for two surface conditions with transition fixed by a thread at 5 percent chord back of the leading edge on the upper and lower surfaces. Below the Mach number at which shock occurred, variations in Mach number of as much as 0.16 appeared to have no appreciable effect on the section profile-… more
Date: September 1944
Creator: Zalovcik, John A. & Wood, Clotaire
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static-Pressure Error of an Airspeed Installation on an Airplane in High-Speed Dives and Pullouts

Description: "Tests were made in high-speed dives and pull-outs to determine, by combined radar-optical tracking equipment, the static-pressure error of an airspeed-head installation on a P-51B airplane." The equipment used and testing procedure are described. The variation of static-pressure error is provided for several ranges of airplane lift coefficient.
Date: February 1946
Creator: Zalovcik, John A. & Wood, Clotaire
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by the use of accelerometer and attitude-angle measurements

Description: A method is described for calibrating airspeed installation on airplanes at transonic and supersonic speeds in vertical-plane maneuvers in which use is made of measurements of normal and longitudinal accelerations and attitude angle. In this method all the required instrumentation is carried within the airplane. An analytical study of the effects of various sources of error on the accuracy of an airspeed calibration by the accelerometer method indicated that the required measurements can be mad… more
Date: December 5, 1952
Creator: Zalovcik, John A.; Lina, Lindsay J. & Trant, James P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Boundary-Layer Control by Suction Slots on an NACA 35-215 Low-Drag Airfoil at High Reynolds Numbers

Description: Report presenting an investigation of the effectiveness of suction slots as a means of extending the laminar boundary layer in flight at high Reynolds numbers on an NACA 35-215 airfoil. The results showed that, with a slot spacing of about 5 percent of the chord, the laminar boundary layer could be maintained to or slightly beyond 45 percent of the chord.
Date: February 1944
Creator: Zalovcik, John A.; Wetmore, J. W. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Description: Report presenting an investigation of the effectiveness of suction slots a a means of extending the laminar boundary layer in flight at high Reynolds numbers using an NACA 35-215 airfoil. Tests were made over a range of indicated airspeeds, lift coefficients, and Reynolds numbers. Results regarding boundary-layer control, air-intake distributions, character of the boundary layer, total-intake rate, and profile-drag coefficient are provided.
Date: February 1944
Creator: Zalovcik, John A.; Wetmore, J. W. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Artificial Aging of Riveted Joints Made in Alclad 24S-T Sheet Using A17S-T, 17S-T, and 24S-T Rivets

Description: Note presenting an investigation of the effect of artificial aging on the strengths of driven rivets of the alloys used commercially for rivets: specifically, A17S-T, 17S-T, and 24S-T. The change in shear strength for each type of rivet after being exposed to artificial aging treatment of 10 hours at 375 degrees Fahrenheit applied to the driven rivets is described.
Date: September 1944
Creator: Zamboky, A. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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System Analyses and Autopilot Design for Automatic Roll Stabilization of a Supersonic Pilotless Aircraft

Description: Memorandum presenting system analyses and autopilot design procedure for a supersonic pilotless aircraft with twin jet engines. The autopilots investigated were a gyro-actuated control, a gyro-actuated control with a rate-sensing device, and an electronic-hydraulic autopilot. Results regarding the airframe and gyro-actuated control system; airframe, gyro-actuated control, and rate servo; airframe and electronic-hydraulic autopilot; and contribution of method of analysis to system design are pro… more
Date: July 11, 1951
Creator: Zarovsky, Jacob
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight investigation of a roll-stabilized missile configuration at varying angles of attack at Mach numbers between 0.8 and 1.79

Description: A missile research model was flown at supersonic speed to determine the quality of automatic roll stabilization at varying angles of attack. Aerodynamic rolling and pitching derivatives were determined from the flight record. It was concluded that the combination of the gyro-actuated automatic pilot with wing-tip ailerons provided adequate roll stabilization under conditions encountered in flight.
Date: January 1957
Creator: Zarovsky, Jacob & Gardiner, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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