Transonic Unsteady Aerodynamic and Aeroelastic Calculations about Airfoils and Wings
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Page : 16 pages
File Size : 15,9 MB
Release : 1987
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Page : 16 pages
File Size : 15,9 MB
Release : 1987
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Page : 38 pages
File Size : 11,47 MB
Release : 1984
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Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 36 pages
File Size : 24,83 MB
Release : 2018-08-16
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ISBN : 9781725624498
The development and application of transonic small disturbance codes for computing two dimensional flows, using the code ATRAN2, and for computing three dimensional flows, using the code ATRAN3S, are described. Calculated and experimental results are compared for unsteady flows about airfoils and wings, including several of the cases from the AGARD Standard Aeroelastic Configurations. In two dimensions, the results include AGARD priority cases for the NACA 64A006, NACA 64A010, NACA 0012, and MBB-A3 airfoils. In three dimensions, the results include flows about the F-5 wing, a typical wing, and the AGARD rectangular wings. Viscous corrections are included in some calculations, including those for the AGARD rectangular wing. For several cases, the aerodynamic and aeroelastic calculations are compared with experimental results. Goorjian, P. M. and Guruswamy, G. P. Ames Research Center NASA-TM-85986, A-9822, NAS 1.15:85986 RTOP 505-31-01...
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Page : 684 pages
File Size : 16,57 MB
Release : 1989
Category : Aerodynamics, Transonic
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Page : 14 pages
File Size : 18,74 MB
Release : 1987
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Page : 14 pages
File Size : 22,11 MB
Release : 1985
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Author : S. Y. Ruo
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Page : 60 pages
File Size : 22,54 MB
Release : 1975
Category : Aerodynamics, Transonic
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An analytical approach is presented to account for some of the nonlinear characteristics of the transonic flow equation for finite thickness wings undergoing harmonic oscillation at sonic flight speed in an inviscid, shock-free fluid. The thickness effect is accounted for in the analysis through use of the steady local Mach number distribution over the wing at its mean position by employing the local linearization concept and a coordinate transformation. Computed results are compared with that of the linearized theory and experiments. Based on the local linearization concept, an alternate formulation avoiding the limitations of the coordinate transformation method is presented.
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Page : 276 pages
File Size : 47,9 MB
Release : 1989
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Page : 14 pages
File Size : 32,33 MB
Release : 1988
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Page : 24 pages
File Size : 42,12 MB
Release : 1985
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The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 deg and 67.5 deg; respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg sweep case and also for small angles of attack at the 67.5 deg sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.