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A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow
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Book Synopsis A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow by : Frank Herman Durgin
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 94 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.
Book Synopsis A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow by : Frank Herman Durgin
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.
Book Synopsis Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45° Wing in Supersonic Flow by : Floyd V. Bennett
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.
Book Synopsis Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique by : National Aeronaut Administration (Nasa)
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 Aeronaut Administration (Nasa) and published by . This book was released on 2020-08-18 with total page 58 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 NASA/TM-2013-217977, L-20228, NF1676L-16083 AERODYNAMIC LOADS; ANGLE OF ATTACK; DYNAMIC PRESSURE; MACH NUMBER; STATIC PRESSURE; TRAILING EDGE FLAPS; OPTICAL MEASUREMENT; REYNOLDS NUMBER; WIND TUNNELS; FLEXIBLE WINGS; PHOTOGRAMMETRY
Book Synopsis Supersonic Aeroelastic Effects on Static Stability and Control: Aeroelastic interaction, by V. W. Donato by : Bell Aircraft Corporation
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:
Book Synopsis Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique by : Gary E. Erickson
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.
Book Synopsis Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Degree Delta Wing in Supersonic Flow by : FLOYD V. BENNETT
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).
Book Synopsis U.S. Government Research Reports by :
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:
Book Synopsis Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Delta Wing in Supersonic Flow by : Floyd V. Bennett
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:
Book Synopsis Proceedings of Symposium on Aeroelastic & Dynamic Modeling Technology, 23-24-25 September 1963, Dayton, Ohio by :
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:
Book Synopsis The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms by : Max A. Heaslet
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.
Book Synopsis Index of NASA Technical Publications by : United States. National Aeronautics and Space Administration
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:
Book Synopsis Experimental investigation of aeroelastic deformation of slender wings at supersonic speeds using a video model deformation measurement technique by : Gary E. Erickson
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:
Book Synopsis Supersonic Aeroelastic Instability Results for a NASP-like Wing Model by :
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:
Book Synopsis Technical Abstract Bulletin by : Defense Documentation Center (U.S.)
Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1961-02 with total page 1116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1960 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt:
