Download or read book Low speed Airspeed Calibration Data for a Single engine Research support Aircraft written by and published by . This book was released on 1980 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Information Output of the Langley Research Center for Calendar Year written by and published by . This book was released on 1981 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Information Output of the Langley Research Center for Calendar Year 1980 written by and published by . This book was released on 1981 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Paper written by and published by . This book was released on 1984 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 NASA Technical Memorandum written by and published by . This book was released on 1981 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1992 with total page 548 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 Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)

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 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 Government Reports Announcements Index written by and published by . This book was released on 1980 with total page 1402 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Natural Laminar Flow Experiments on Modern Airplane Surfaces written by Bruce J. Holmes and published by . This book was released on 1984 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Air Data Position error Calibration Using State Reconstruction Techniques written by and published by . This book was released on 1984 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Using Global Positioning for Air Data System Calibration of General Aviation Aircraft Have Pacer II written by and published by . This book was released on 1996 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of an evaluation of the suitability of using handheld Global Positioning System (GPS) receivers using course acquisition code to perform an air data system calibration. The two testbeds were an aerospatiale Tobago and a Rutan Long EZ, both general aviation single engine land aircraft. The test objective was to evaluate the suitability of commercial GPS receivers as measuring devices for general aviation air data system (ADS) calibration. Emphasis was on a handheld GPS and data collection devices. The goal was to develop a technique to accomplish an ADS calibration on a low-speed (under 200 knots calibrated airspeed) aircraft, using only commercial GPS equipment. After an all-altitude airspeed comparison technique was developed, a calibration of the ADS of an uninstrumented general aviation aircraft was completed. Overall, the commercial OPS receivers were suitable as measurement devices for ADS calibrations. Any current, commercially available receiver could be used without the need for differential GPS receivers or rigorous postprocessing of receiver data.