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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 : 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.
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.
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:
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:
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 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:
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.
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 22 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.
