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Some Flight Measurements Of Pressure Distribution During Tail Buffeting
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Book Synopsis Some Flight Measurements of Pressure Distribution During Tail Buffeting by : John Boshar
Download or read book Some Flight Measurements of Pressure Distribution During Tail Buffeting written by John Boshar and published by . This book was released on 1945 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of pressure-distribution measurements taken over the horizontal tail surfaces of a Curtiss P-40K airplane during several low-speed pull-ups to abrupt stall in which tail buffeting was experienced.
Book Synopsis Some Flight Measurement of Pressure Distribution During Tail Buffeting by : John Boshar
Download or read book Some Flight Measurement of Pressure Distribution During Tail Buffeting written by John Boshar and published by . This book was released on 1945 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Studies of the Horizontal-tail Loads Experienced by a Modern Pursuit Airplane in Abrupt Maneuvers by : Langley Aeronautical Laboratory
Download or read book Flight Studies of the Horizontal-tail Loads Experienced by a Modern Pursuit Airplane in Abrupt Maneuvers written by Langley Aeronautical Laboratory and published by . This book was released on 1944 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Flight measurements were made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of the fluctuating tail loads in accelerated stalls. The results indicated that, if the airplane were not stalled, a total up load of 5700 pounds would be experienced on the horizontal tail in an 8g pull-up and that, with power on, this load would be distributed unsymmetrically with about 800 pounds more up load on the left stabilizer than on the right. When stalling occurred there was an initial abrupt increase in the up tail load of the order of 100 percent of the previous load, which was followed by repeated load and stress variations due to tail buffeting. Under the condition of tail buffeting, the possibility of excessive stresses due to resonance was indicated.
Book Synopsis NACA Wartime Report by : United States. National Advisory Committee for Aeronautics
Download or read book NACA Wartime Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 716 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wartime Report written by and published by . This book was released on 194? with total page 622 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
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 1959 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wartime Report by : United States. National Advisory Committee for Aeronautics
Download or read book Wartime Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 440 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical Method of Determining Transmission of Particles and Radiation Through Great Thickness of Matter by : A. R. Bobrowsky
Download or read book Analytical Method of Determining Transmission of Particles and Radiation Through Great Thickness of Matter written by A. R. Bobrowsky and published by . This book was released on 1948 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt: A matrixc method of determining transmission, scattering, and absorption of radition, such as gamma rays and neutrons, is presented in this report.
Book Synopsis Measurements of the Pressure Distribution on the Horizontal-tail Surface of a Typical Propeller-driven Pursuit Airplane in Flight by : Melvin Sadoff
Download or read book Measurements of the Pressure Distribution on the Horizontal-tail Surface of a Typical Propeller-driven Pursuit Airplane in Flight written by Melvin Sadoff and published by . This book was released on 1947 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution measurements were made in steady straight and accelerated flight over both sides of the horizontal-tail surface of a typical pursuit airplane up to a Mach number of 0.79. The results showed that a sharply increasing down-load was required to balance the increased diving moment of the wing-fuselage-propeller group at Mach numbers above about 0.70. There was little change, up to a Mach number of about 0.65, of the tail-load gradient (rate of increase of tail load for a unit change in acceleration factor); beyond that Mach number, however, a rapid decrease of tail-load gradient to a Mach number of about 0.73 and then a very sharp increase up to a Mach number of 0.785 was noted. The root bending moments increased considerably on the right tail and decreased, to a lesser extent, on the left tail at the higher Mach numbers, resulting in increased fuselage torsional moments at high speeds. At the higher values of lift coefficient (0.5 to 0.8), there was little change of the lateral distance to the center pressure up to a Mach number of about 0.73; at the highest speed and at low lift coefficients (0 to 0.1) the center of pressure was inboard approximately 3 feet on the left tail and 1.5 feet on the right tail as compared with the values at lower speeds. It appears that satisfactory quantitative data on total tail loads may be obtained from measurements at four stations, equally spaced along the entire tail span.
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
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 1949 with total page 816 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Studies of the Horizontal-tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers by : Langley Aeronautical Laboratory
Download or read book Flight Studies of the Horizontal-tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers written by Langley Aeronautical Laboratory and published by . This book was released on 1944 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of the fluctuating tail loads in accelerated stalls. The results indicated that, if the airplane were not stalled, a total up load of 5700 pounds would be experienced on the horizontal tail in an 8g pull-up and that, with power on, this load would be distributed unsymmetrically with about 800 pounds more up load on the left stabilizer than on the right. When stalling occurred there was an initial abrupt increase in the up tail load of the order of 100 percent of the previous load, which was followed by repeated load and stress variations due to tail buffeting. Under the condition of tail buffeting, the possibility of excessive stresses due to resonance was indicated.
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1949 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of the Pressure Distribution on the Horizontal-tail Surface of a Typical Propeller-driven Pursuit Airplane in Flight by :
Download or read book Measurements of the Pressure Distribution on the Horizontal-tail Surface of a Typical Propeller-driven Pursuit Airplane in Flight written by and published by . This book was released on 1948 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: The total horizontal-tail load and root bending-moment increments calculated by the use of existing rational procedures are compared with the experimental values obtained in abrupt pull-up push-down maneuvers obtained on a representative pursuit-type airplane. The computed loads were determined for the experimental motions and for two estimated linear design motions. The results showed that the actual maximum maneuvering tail loads obtainable in flight could be predicted satisfactorily from either the experimental elevator motions measured in the maneuvers of from the estimated linear elevator motions, provided that good quantitative knowledge was had of pertinent aerodynamic parameters.
Book Synopsis Wartime Report Release List by : United States. National Advisory Committee for Aeronautics
Download or read book Wartime Report Release List written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1947 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Measurements on An F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 4. Buffet Cross Spectral Densities by :
Download or read book Pressure Measurements on An F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 4. Buffet Cross Spectral Densities written by and published by . This book was released on 1994 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt: Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to PSD and CSD forms. Both steady and unsteady RMS pressure coefficients are also presented. Volume 1 contains the general description of the model, the test program, and highlights of the reduced data. Volume 2 contains steady and unsteady RMS data. Volume 3 contains unsteady PSD results. Volume 4 contains unsteady CSD results. Unsteady aerodynamics, Buffeting flow, Pressure measurements, Wind tunnel tests, Experimental data, Pressure transducers.
Book Synopsis Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 3. Buffet Power Spectral Densities by :
Download or read book Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 3. Buffet Power Spectral Densities written by and published by . This book was released on 1994 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to PSD and CSD forms. Both steady and unsteady RMS pressure coefficients are also presented. Volume 1 contains the general description of the model, the test program, and highlights of the reduced data. Volume 2 contains steady and unsteady RMS data. Volume 3 contains unsteady PSD results. Volume 4 contains unsteady CSD results. Unsteady aerodynamics, Buffeting flow, Pressure measurements, Wind tunnel tests, Experimental data, Pressure transducers.
Book Synopsis The Measurement of the Pressure Distribution Over the Wing of an Aircraft in Flight by :
Download or read book The Measurement of the Pressure Distribution Over the Wing of an Aircraft in Flight written by and published by . This book was released on 2008 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A measurement system has been developed for use on a light aircraft to measure the pressure distribution over the wing surfaces. The measurement system was developed as a low-cost alternative to existing advanced measurement systems. The system consisted of low profile, low cost pressure sensors that interfaced digitally with microcontrollers for data acquisition. The pressure sensors and microcontrollers were developed into self-contained sensor modules with all electronic components mounted on flexible circuit board that formed the base of the modules. Two types of module were developed; a module with a single pressure sensor and a module with a row of seven pressure sensors at fifteen millimetre spacing. The total cost of the sensor modules was approximately ninety dollars for a single sensor module and one hundred and forty dollars for the seven sensor module. Studies were carried out using numerical methods to predict the pressure distribution over a NACA2412 airfoil. The numerical studies were used to evaluate the effect of adding the sensor modules to the wing, and the effect of the sensor distribution on measured force coefficients. Numerical predictions were made using the XFOIL software package. This software was validated using the Hess-Smith inviscid panel method. Flight testing was carried out with the pressure distribution measurement system to confirm the operation of the system and to make preliminary measurements. The flight testing focused on the measurement of steady state pressure distributions for comparison with the numerical predictions. Good agreement was found between the measured pressure distributions and the XFOIL predictions. Integration of the pressure distributions enabled comparison of normal force, lift force and quarter chord moment coefficients. The measured force coefficients showed the expected trends with angle of attack although it was found that the limited number of sensor modules used caused large error in the quarter chord moment coefficient compared to the numerical predictions.
