Download or read book A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow written by Frank Herman Durgin and published by . This book was released on 1963 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aeroelastic analysis of Zisfein, Donato and Farrell (AD-155739) uses an aerodynamic matrix, a structural matrix and the initial angle of attack to predict the equilibrium pressures and shape of a wing. To test the accuracy of their methods, a flexible wing was built and instrumented with pressure taps and mirrors. The wing was tested at Mach numbers of 2 and 3, and both the pressure distribution and the deflected shape were measured. An aerodynamic matrix computed on the basis of the semiempirical procedures of the above authors was used to predict pressure distributions, and an experimentally determined structural matrix was used to find equilibrium angles of attack. Finally, these two matrices were used in the aeroelastic equations to compute pressures and angles of attack from the undeflected shape of the wing. Comparisons between theory and experiment are presented for eight different free stream conditions. -- page iii.

Download or read book Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Wing in Supersonic Flow written by Floyd V. Bennett and published by . This book was released on 1961 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests showing the effects of static aeroelasticity for a thin 45° delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results.

Download or read book Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-23 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: A video-based photogrammetric model deformation system was established as a dedicated optical measurement technique at supersonic speeds in the NASA Langley Research Center Unitary Plan Wind Tunnel. This system was used to measure the wing twist due to aerodynamic loads of two supersonic commercial transport airplane models with identical outer mold lines but different aeroelastic properties. One model featured wings with deflectable leading- and trailing-edge flaps and internal channels to accommodate static pressure tube instrumentation. The wings of the second model were of single-piece construction without flaps or internal channels. The testing was performed at Mach numbers from 1.6 to 2.7, unit Reynolds numbers of 1.0 million to 5.0 million, and angles of attack from -4 degrees to +10 degrees. The video model deformation system quantified the wing aeroelastic response to changes in the Mach number, Reynolds number concurrent with dynamic pressure, and angle of attack and effectively captured the differences in the wing twist characteristics between the two test articles. Erickson, Gary E. Langley Research Center AERODYNAMIC LOADS; ANGLE OF ATTACK; DYNAMIC PRESSURE; MACH NUMBER; STATIC PRESSURE; TRAILING EDGE FLAPS; OPTICAL MEASUREMENT; REYNOLDS NUMBER; WIND TUNNELS; FLEXIBLE WINGS; PHOTOGRAMMETRY

Download or read book Supersonic Aeroelastic Effects on Static Stability and Control Aeroelastic interaction by V W Donato written by Bell Aircraft Corporation and published by . This book was released on 1958 with total page 374 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique written by Gary E. Erickson and published by BiblioGov. This book was released on 2013-06 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: A video-based photogrammetric model deformation system was established as a dedicated optical measurement technique at supersonic speeds in the NASA Langley Research Center Unitary Plan Wind Tunnel. This system was used to measure the wing twist due to aerodynamic loads of two supersonic commercial transport airplane models with identical outer mold lines but different aeroelastic properties. One model featured wings with deflectable leading- and trailing-edge flaps and internal channels to accommodate static pressure tube instrumentation. The wings of the second model were of single-piece construction without flaps or internal channels. The testing was performed at Mach numbers from 1.6 to 2.7, unit Reynolds numbers of 1.0 million to 5.0 million, and angles of attack from -4 degrees to +10 degrees. The video model deformation system quantified the wing aeroelastic response to changes in the Mach number, Reynolds number concurrent with dynamic pressure, and angle of attack and effectively captured the differences in the wing twist characteristics between the two test articles.

Download or read book Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Degree Delta Wing in Supersonic Flow written by FLOYD V. BENNETT and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel data showing the effects of static aeroelasticity are presented and compared with theory in the Mach number range 1.30 to 4.00. Calculated deformation, normal-force coefficients, and pitching-moment coefficients based on linearized potential theory are shown to compare favorably with the wind-tunnel results. Calculations are also made at Mach numbers of 3.00 and 4.00 based on piston theory and on a modification of piston theory. (Author).

Download or read book U S Government Research Reports written by and published by . This book was released on 1964 with total page 1416 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Delta Wing in Supersonic Flow written by Floyd V. Bennett and published by . This book was released on 1961 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Max A. Heaslet and published by . This book was released on 1948 with total page 726 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.

Download or read book Proceedings of Symposium on Aeroelastic Dynamic Modeling Technology 23 24 25 September 1963 Dayton Ohio written by and published by . This book was released on 1964 with total page 800 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental investigation of aeroelastic deformation of slender wings at supersonic speeds using a video model deformation measurement technique written by Gary E. Erickson and published by . This book was released on 2013 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1961 with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Aeroelastic Instability Results for a NASP like Wing Model written by and published by . This book was released on 1993 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Fluctuating Loads Measured on an Over the wing Supersonic Jet Model written by Conrad M. Willis and published by . This book was released on 1979 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fluctuating pressure loads on the wing and flap of an over-the-wing supersonic jet model were measured. The model was tested statically and at a Mach number of 0.1 in a small free jet to simulate forward speed. Test parameters were impingement angle, nozzle height, and flap deflection. Load levels as high as 170 db were measured at the center of the impingement region during static tests. Forward speed reduced the loading about 1 db. Load level increased with increasing impingement angle and decreasing nozzle height above the wing. The effect of flap deflection was small. When scaled to full-size aircraft conditions, the maximum amplitude of the one-third-octave fluctuating pressure spectra was about 154 db at about 160 Hz. Maximum load level occurred near the intersection of the nozzle center line with the impinged surface. Downstream of the maximum the fluctuating pressure is inversely proportional to the distance downstream of the nozzle.

Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page 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 500 pages. Available in PDF, EPUB and Kindle. Book excerpt: