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.

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.

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.

Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 894 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NACA Research Memorandum written by and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1954 with total page 818 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Free Convection on a Vertical Plate with Prescribed Nonuniform Wall Heat Flux Or Prescribed Nonuniform Wall Temperature written by Ephraim M. Sparrow and published by . This book was released on 1955 with total page 744 pages. Available in PDF, EPUB and Kindle. Book excerpt: All the aforementioned results are given for fluids having Prandtl numbers in the range 0.01 to 1000.

Download or read book A Flight Evaluation of the Longitudinal Stability Characteristics Associated with the Pitch up of a Swept wing Airplane in Maneuvering Flight at Transonic Speeds written by Charles E. Watkins and published by . This book was released on 1955 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Report written by and published by . This book was released on 1955 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

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.

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:

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.

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.