Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 976
Book Description
Journal of the Royal Aeronautical Society
Author: The Journal of the Royal Aeronautical Society
Author: Royal Aeronautical SocietyPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 962
Book Description
Measurement of Aircraft Speed and Altitude
Author: William GraceyPublisher: John Wiley & Sons
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 288
Book Description
Flight Calibration of Four Airspeed Systems on a Swept-wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-phototheodolite Method
Author: Jim Rogers ThompsonPublisher:
ISBN:
Category : Air-speed indicators
Languages : en
Pages : 46
Book Description
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.
Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
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.
Flight Calibration of Four Airspeed Systems on a Swept-Wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-Phototheodolite Method
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
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.
Aerospace Engineering Index
Author: Aeronautical Engineering Index
Author: Cumulative Title Index to United States Public Documents, 1789-1976
Author: Daniel W. LesterPublisher:
ISBN:
Category : Government publications
Languages : en
Pages : 544
Book Description
Memoirs of an Aeronautical Engineer
Author: Seth B AndersonPublisher: Legare Street Press
ISBN: 9781016086967
Category :
Languages : en
Pages : 0
Book Description
This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work is in the "public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.