Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Flight Calibration Of Four Airspeed Systems On A Swept Wing Airplane At Mach Numbers Up To 104 By The Naca Radar Phototheodolite Method
Download Flight Calibration Of Four Airspeed Systems On A Swept Wing Airplane At Mach Numbers Up To 104 By The Naca Radar Phototheodolite Method full books in PDF, epub, and Kindle. Read online Flight Calibration Of Four Airspeed Systems On A Swept Wing Airplane At Mach Numbers Up To 104 By The Naca Radar Phototheodolite Method ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Flight Calibration of Four Airspeed Systems on a Swept-wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-phototheodolite Method by : Jim Rogers Thompson
Download or read book Flight Calibration of Four Airspeed Systems on a Swept-wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-phototheodolite Method written by Jim Rogers Thompson and published by . This book was released on 1950 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Of the systems investigated, a nose-boom installation was found to be most suitable for research use at transonic and low supersonic speeds because it provided the greatest sensitivity of the indicated Mach number to a unit change in true Mach number at very high subsonic speeds, and because it was least sensitive to changes in airplane normal-force coefficient. The static-pressure error of the nose-boom system was small and constant above a Mach number of 1.03 after passage of the fuselage bow shock wave over the airspeed head.
Book Synopsis Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method by :
Download or read book Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method written by and published by . This book was released on 1955 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The calibrations of four airspeed systems installed in a North American F-86A airplane have been determined in flight at Mach numbers up to 1.04 by the NACA radar-phototheodolite method. The variation of the static-pressure error per unit indicated impact pressure is presented for three systems typical of those currently in use in flight research, a nose boom and two different wing-tip booms, and for the standard service system installed in the airplane. A limited amount of information on the effect of airplane normal-force coefficient on the static-pressure error is included. The results are compared with available theory and with results from wind-tunnel tests of the airspeed heads alone. Of the systems investigated, a nose-boom installation was found to be most suitable for research use at transonic and low supersonic speeds because it provided the greatest sensitivity of the indicated Mach number to a unit change in true Mach number at very high subsonic speeds, and because it was least sensitive to changes in airplane normal-force coefficient. The static-pressure error of the nose-boom system was small and constant above a Mach number of 1.03 after passage of the fuselage bow shock wave over the airspeed head.
Book Synopsis Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method by :
Download or read book Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method written by and published by . This book was released on 1955 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The calibrations of four airspeed systems installed in a North American F-86A airplane have been determined in flight at Mach numbers up to 1.04 by the NACA radar-phototheodolite method. The variation of the static-pressure error per unit indicated impact pressure is presented for three systems typical of those currently in use in flight research, a nose boom and two different wing-tip booms, and for the standard service system installed in the airplane. A limited amount of information on the effect of airplane normal-force coefficient on the static-pressure error is included. The results are compared with available theory and with results from wind-tunnel tests of the airspeed heads alone. Of the systems investigated, a nose-boom installation was found to be most suitable for research use at transonic and low supersonic speeds because it provided the greatest sensitivity of the indicated Mach number to a unit change in true Mach number at very high subsonic speeds, and because it was least sensitive to changes in airplane normal-force coefficient. The static-pressure error of the nose-boom system was small and constant above a Mach number of 1.03 after passage of the fuselage bow shock wave over the airspeed head.
Book Synopsis Measurement of Aircraft Speed and Altitude by : William Gracey
Download or read book Measurement of Aircraft Speed and Altitude written by William Gracey and published by John Wiley & Sons. This book was released on 1981 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of the Royal Aeronautical Society by :
Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1956 with total page 976 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Journal of the Royal Aeronautical Society by : Royal Aeronautical Society
Download or read book The Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1956 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Airspeed Calibrations Evaluated by the Accelerometer and Radar Methods by : Lindsay J. Lina
Download or read book Comparison of Airspeed Calibrations Evaluated by the Accelerometer and Radar Methods written by Lindsay J. Lina and published by . This book was released on 1952 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Airspeed calibration of the pitot-static installation on a jet fighter airplane was made to compare the accelerometer method of determining the static-pressure error with the radar method. The tests included shallow dives up to a Mach number of about 0.80 with pull-ups of about 4, 3, and 2g normal acceleration. The results of the test indicated that, for vertical plane maneuvers, the accelerometer method may be used as an alternate to the radar method.
Download or read book Aerospace Engineering Index written by and published by . This book was released on 1958 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Cumulative Title Index to United States Public Documents, 1789-1976 by : Daniel W. Lester
Download or read book Cumulative Title Index to United States Public Documents, 1789-1976 written by Daniel W. Lester and published by . This book was released on 1980 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering Index written by and published by . This book was released on 1954 with total page 1212 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Accuracy of Airspeed Measurements and Flight Calibration Procedures by : Wilber B. Huston
Download or read book Accuracy of Airspeed Measurements and Flight Calibration Procedures written by Wilber B. Huston and published by . This book was released on 1948 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report reviews in detal the sources of error that may enter into the measurement of airspeed by pitot-static methods. Methods of flight calibration of airspeed installations are given. Special attention is given to the problem of accurate measurement of Mach number, air temperature, and true airspeed during high-speed maneuvers. This report also contains an extensive bibliography.
Book Synopsis A Radar Method of Calibrating Airspeed Installations on Airplanes in Maneuvers at High Altitudes and at Transonic and Supersonic Speeds by : John A. Zalovcik
Download or read book A Radar Method of Calibrating Airspeed Installations on Airplanes in Maneuvers at High Altitudes and at Transonic and Supersonic Speeds written by John A. Zalovcik and published by . This book was released on 1950 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Flight Calibration of Compensated and Uncompensated Pitot-static Airspeed Probes and Application of the Probes to Supersonic Cruise Vehicles by : Lannie D. Webb
Download or read book Flight Calibration of Compensated and Uncompensated Pitot-static Airspeed Probes and Application of the Probes to Supersonic Cruise Vehicles written by Lannie D. Webb and published by . This book was released on 1972 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static pressure position error calibrations for a compensated and an uncompensated XB-70 nose boom pitot static probe were obtained in flight. The methods (Pacer, acceleration-deceleration, and total temperature) used to obtain the position errors over a Mach number range from 0.5 to 3.0 and an altitude range from 25,000 feet to 70,000 feet are discussed. The error calibrations are compared with the position error determined from wind tunnel tests, theoretical analysis, and a standard NACA pitot static probe. Factors which influence position errors, such as angle of attack, Reynolds number, probe tip geometry, static orifice location, and probe shape, are discussed. Also included are examples showing how the uncertainties caused by position errors can affect the inlet controls and vertical altitude separation of a supersonic transport.
Book Synopsis Error in Airspeed Measurement Due to Static-pressure Field Ahead of the Wing Tip of a Swept-wing Airplane Model at Transonic Speeds by : Edward C. B. Danforth
Download or read book Error in Airspeed Measurement Due to Static-pressure Field Ahead of the Wing Tip of a Swept-wing Airplane Model at Transonic Speeds written by Edward C. B. Danforth and published by . This book was released on 1951 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made at or near zero lift.
Book Synopsis An Analysis of Incremental Horizontal-tail Loads Measured on a Swept-wing Bomber Airplane in Sideslip Maneuvers by : William A. McGowan
Download or read book An Analysis of Incremental Horizontal-tail Loads Measured on a Swept-wing Bomber Airplane in Sideslip Maneuvers written by William A. McGowan and published by . This book was released on 1959 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Position Errors of the Service Airspeed Installations of 10 Airplanes by : William Gracey
Download or read book Position Errors of the Service Airspeed Installations of 10 Airplanes written by William Gracey and published by . This book was released on 1949 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: The "position" errors of the static systems of 10 service airspeed installations including static-pressure vents on the nose and rear section of the fuselage and pitot-static tubes mounted on the wing, the vertical tail, and the fuselage nose are presented. Tests were conducted at speeds between the stalling speed and 260 miles per hour for four flight conditions. Calibrations are analyzed to show variation of static-pressure error with position of static source, angle of attack, flap setting, and engine power.
Book Synopsis Flight Calibration of Angle-of-attack and Sideslip Detectors on the Fuselage of a 35 Degree Swept-wing Fighter Airplane by : Norman M. McFadden
Download or read book Flight Calibration of Angle-of-attack and Sideslip Detectors on the Fuselage of a 35 Degree Swept-wing Fighter Airplane written by Norman M. McFadden and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
