WorldCat Identities

Zalovcik, John A.

Overview
Works: 42 works in 76 publications in 1 language and 176 library holdings
Classifications: TL507,
Publication Timeline
Key
Publications about  John A Zalovcik Publications about John A Zalovcik
Publications by  John A Zalovcik Publications by John A Zalovcik
Most widely held works by John A Zalovcik
Comparison of VGH data from wide-body and narrow-body long-haul turbine-powered transports by John A Zalovcik ( Book )
4 editions published in 1977 in English and held by 67 WorldCat member libraries worldwide
NASA research on noise-abatement approach profiles for multiengine jet transport aircraft by John A Zalovcik ( Book )
3 editions published in 1967 in English and held by 23 WorldCat member libraries worldwide
Effect of thrust and altitude in steep approaches on ground track noise by John A Zalovcik ( Book )
3 editions published in 1967 in English and held by 10 WorldCat member libraries worldwide
A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by use of accelerometer and attitude-angle measurements by John A Zalovcik ( Book )
4 editions published in 1950 in English and held by 6 WorldCat member libraries worldwide
A method is described for calibrating airspeed installations 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. The required instrumentation is carried within the airplane. The various sources of error are also discussed
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight by John A Zalovcik ( Book )
4 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
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
Flight investigation of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane by John A Zalovcik ( Book )
3 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
Summary: A flight investigation was 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 were made on the upper surface of the left wing in the slip-stream at 25 percent semispan; pressure-distribution measurements were made on the upper surface of the left wing at 63 percent semispan; and wake surveys were made at 63 percent semispan of the right wing. The tests were made in straight flight and in turns over a range of conditions in which airplane lift coefficients from 0.15 to 0.68, Reynolds numbers from 7.7 x 10⁶ to 19.7 x 10⁶, and Mach numbers from 0.25 to 0.69 were obtained. The results of the investigation indicated a minimum profile-drag coefficient of 0.0062 for the smooth section at 63 percent semispan. At the highest Mach number attained in the tests, the critical Mach number was exceeded by at least 0.04 with no evidence of compressibility shock losses appearing in the form of increased width of the wake or increased profile-drag coefficient. For flight conditions approaching the critical Mach number, variations in Mach number of as much as 0.17 appeared to have no effect on the profile-drag coefficient. In the slipstream, transition occurred at least as far back as 20 percent chord on the upper surface at low lift coefficients
A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by the use of accelerometer and attitude-angle measurements by John A Zalovcik ( Book )
3 editions published in 1953 in English and held by 4 WorldCat member libraries worldwide
A Radar method of calibrating airspeed installations on airplanes in maneuvers at high altitudes and at transonic and supersonic speeds by John A Zalovcik ( Book )
3 editions published in 1949 in English and held by 4 WorldCat member libraries worldwide
A method for calibrating the static-pressure source of a pitot-static airspeed installation on the airplane in level flight, dives, and other maneuvers is described. The method principally involves the use of radar-phototheodolite tracking equipmment and is particularly suited for higher speeds at high altitudes. The accuracy of the method is discussed and sample calibrations are included
A radar method of calibrating airspeed installations on airplanes in maneuvers at high altitudes and at transonic and supersonic speeds by John A Zalovcik ( Book )
4 editions published between 1949 and 1950 in English and held by 4 WorldCat member libraries worldwide
Summary of stall-warning devices by John A Zalovcik ( Book )
3 editions published between 1952 and 1995 in English and held by 3 WorldCat member libraries worldwide
Principles involved in the operation of stall-warning devices are described and conditions under which difficulty may be experienced are pointed out. Some specific examples of stall-warning devices are illustrated and described
Calculated effect some of some airplane handling techniques on the ground-run distance in landing on slippery runways by John A Zalovcik ( Book )
2 editions published in 1957 in English and held by 3 WorldCat member libraries worldwide
Some calculations were 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 severla types of jet airplanes on slippery runways. The airplanes considered were a swept-wing transport and unswept-, swept-, and delta-wing fighters. The effect of such factors as speed, braking effectiveness, and residual thrust on the difference in ground-run distance with the two-handling techniques is briefly considered. Some computations were also made to indicate the effect of instantaneous flap retraction on the ground-run distance
Static-pressure error of an airspeed installation on an airplane in high-speed dives and pull-outs by John A Zalovcik ( Book )
3 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide
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 installation included a pitot-static head mounted on a boom 95 percent chord ahead of the leading edge of the wing near the tip. The tests were made in dives at flight Mach numbers up to 0.75 and included pull-outs up to 4g normal acceleration. The results indicated that the static-pressure error did not vary with Mach number by more than about 1 percent of the impact pressure over the range of conditions investigated
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane by John A Zalovcik ( Book )
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
A boundary-layer-transition and profile-drag investigation was conducted in flight by the National Advisory Committee for Aeronautics on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F and supplied by the Army Air Forces. The wing incorporates airfoil section that vary from an NACA 66(215)-1(16.5), a = 1.0 at the plane of symmetry to an NACA 67(115)-213, a = 0.7 at the tip. The surface of the wing as constructed was found to have such a degree of waviness that it had to be refinished in order to obtain the performance generally expected of low-drag airfoils. 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. Tests were made in normal flight - that is, in level flight and in shallow dives - at indicated airspeeds ranging from about 150 to 300 miles per hour and in steady turns at 300 miles per hour with normal acceleration from 2g to 4g. These speed and acceleration limits were imposed by structural considerations. The tests in normal flight covered a range of section lift coefficient from about 0.58 to 0.15, of Reynolds number from about 9 x 10⁶ to 18 x 10⁶, and of Mach number from about 0.27 to 0.53. In the tests in turns at 300 miles per hour, the range of section lift coefficient was extended to 0.63
Flight investigation at high mach numbers of several methods of measuring static pressure on an airplane wing by John A Zalovcik ( Book )
2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
Summary: A flight investigation was made to compare 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 measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory
Flight investigation at high speeds of flow conditions over an airplane wing as indicated by surface tufts by Clotaire Wood ( Book )
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Summary: Flight tests were made at high speeds with a P-47D airplane to determine the flow characteristics, as indicated by wool tufts, on a section of the upper surface of the wing. The behavior of the tufts, which were distributed over a section of the wing from 39.5 to 52.5 percent semispan, was determined from motion pictures. The tests were made in straight flight and in turns under conditions in which airplane lift coefficients from 0.10 to 0.54 and airplane Mach numbers from 0.58 to 0.78 were obtained. The results of the tests indicated that the flow remained smooth over the test panel until the critical Mach number of the panel was exceeded by 0.08 at a lift coefficient of 0.10 and by 0.05 at a lift coefficient of 0.50. Beyond these Mach numbers, the tufts indicated unsteadiness of flow and, finally, local separation when the Mach number exceeded the critical value by 0.13 at a lift coefficient of 0.10 and by 0.10 at a lift coefficient of 0.50. The region of separated flow originated in the neighborhood of 30 percent chord at high lift coefficients and 45 percent chord at low lift coefficients. Separation appeared to extend over not more than 15 percent chord
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint by John A Zalovcik ( Book )
2 editions published in 1946 in English and held by 2 WorldCat member libraries worldwide
Summary: A flight investigation was made at high speeds to determine the profile drag of a P-47D airplane wing having production surfaces covered with camouflage paint. The profile drag of a wing section somewhat out-board of the flap was determined by means of wake surveys in tests made over a range of airplane lift coefficients from 0.06 to 0.69 and airplane Mach numbers from 0.25 to 0.78. The results of the tests 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. Below the Mach number at which compressibility shock occurred, variations in Mach number of as much as 0.2 appeared to have no effect on profile-drag coefficient. The variation in Reynolds number corresponding to this variation in Mach number, however, was appreciable and may have had some effect on the results obtained. Comparison of the Mach number at which shock losses were first evident in the wake with the critical Mach number indicated that shock was not evident until the critical Mach number was exceeded by at least 0.025
NASA research on noise-abatement approach profiles for multiengine jet transport aircraft (National Aeronautics and Space Administration) by United States ( Book )
1 edition published in 1967 in English and held by 2 WorldCat member libraries worldwide
A Method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by use of temperature measurements by John A Zalovcik ( Book )
1 edition published in 1950 in English and held by 2 WorldCat member libraries worldwide
A method of calibrating the static-pressure source of a pitot-static installation of an airplane at transonic and supersonic speeds by use of only instrumentation in the airplane is described. The method involves principally the use of temperature and measurements and is particularly suited for transonic and supersonic speeds at high altitudes. The accuracy of the method is also discussed
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers by John A Zalovcik ( Book )
2 editions published in 1944 in English and held by 2 WorldCat member libraries worldwide
An investigation of the effectiveness of suction slots as a means of extending the laminar boundary layer has been made in flight at Reynolds numbers on an NACA 35-215 airfoil. The test panel, having a chord of 204 inches and an average span of 90 inches, was mounted on the left wing of a Douglas B-18-airplane provided for the tests by the Army Air Corps. The upper surface of the test panel was provided at first with nine spanwise slots and later with eight additional slots, all located between 20 and 60 percent of the chord
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint by John A Zalovcik ( Book )
1 edition published in 1946 in English and held by 1 WorldCat member library worldwide
A flight investigation was made at high speeds to determine the profile drag of a P-47D airplane wing having production surfaces covered with camouflage paint. The profile drag of a wing section somewhat outboard of the flap was determined by means of wake surveys in tests made over a range of airplane lift coefficients from 0.06 to 0.69 and airplane Mach numbers from 0.25 to 0.78
 
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English (54)