Theory and application of an edge gradient system for generating optical transfer functions
Edge gradient analysis for measuring optical transfer functions
Klingman, E.↗
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Quantitative determination of optical imperfections by mathematical analysis of the Foucault knife-edge test pattern
Quantitative determination of optical imperfection by mathematical analysis of Foucault knife edge test pattern in large orbiting telescope
Katzoff, S.↗
Crack shapes and stress intensity factors for edge-cracked specimens
Stress intensity factor and shape of edge crack in plate under tension
Orange, T. W.↗
Computer program for design of two-dimensional sharp-edged-throat supersonic nozzle with boundary layer correction
FORTRAN 4 computer program for design of sharp-edged-throat supersonic nozzles with boundary layer correction
Goldman, L. J.↗
Experimental investigation of leading-edge shock impingement and interaction heating on a 1/80 scale model of a NASA straight wing orbiter configuration at Mach numbers 8 and 16
Leading edge shock impingement and interaction heating on scale model straight wing orbiter
Rogers, C. E.↗
Longitudinal aerodynamic characteristics at Mach 1.50 to 4.63 of a missile model employing various canards and a trailing edge flap control
Wind tunnel static longitudinal stability and control characteristics of cruciform delta winged missile with various horizontal canards and trailing-edge flap control between Mach 1.50 and 4.63
Trescot, C. D., Jr.↗
Subsonic characteristics of a twin-jet swept-wing fighter model with leading edge Krueger flaps
Aerodynamic characteristics of twin jet, swept wing fighter aircraft model with leading edge Kreuger flaps at subsonic speeds
Ray, E. J.↗
Localization in disordered materials - Existence of mobility edges
Disordered materials electronic structure band states localization, examining mobility edges
Cohen, M. H.↗
Estimation of the maximum temperature of a swept leading edge for an equilibrium glide entry
Maximum stagnation temperature on swept wing leading edge for equilibrium glide entry of space shuttle
Crawford, D. H.↗
Mechanical compliance measurements of single- edge-notch tension specimens
Single edge notch tension Al alloy specimens mechanical compliance measurement, solving stress functions for various gage length-sample width combinations
Orloski, M. J.↗
Vortex breakdown on slender sharp-edged wings
Vortex breakdown on slender sharp edged and modified delta wings with varying sweep angles investigated in wind tunnel using schlieren system for flow visualization
Kohlman, D. L.↗
Radiative, ablative, and active cooling thermal protection studies for the leading edge of a fixed-straight wing space shuttle
Performance prediction of fixed wing leading edges radiative, ablative and active cooling thermal protection systems and system weights comparison for space shuttle entry mission
Curry, D. M.↗
On the specification of the blue edge of the RR Lyrae instability strip
Blue edge of RR Lyrae instability strip, examining convection, radiation and surface boundary conditions effects
Iben, I., Jr.↗
Experimental and analytical strains in an edge-cracked sheet
Edge cracked metal sheet elastoplastic strain distribution determination, using optical interference, moire technique and plane stress model finite element method
Kendall, D. P.↗
The resonant response of a rectangular plate with an elastic edge restraint
Peak resonant response of thin rectangular plate with elastic edge restraint under concentrated load
Egle, D. M.↗
Crack shapes and stress intensity factors for edge-cracked specimens
Crack shapes and stress intensity factors for deep edge crack in plate under tension or bending
Orange, T. W.↗
Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds
Pitot-pressure profiles and surface pressure measurements have been obtained at four axial stations along the center lines of space shuttle straight-wing and delta-wing orbiters at angles of attack from 20 deg to approximately 60 deg and Mach numbers of 20.3 (helium) and 6.8 (air). The results show that the Mach number at the edge of the boundary layer is best predicted by tangent-cone theory up to shock detachment.
Ashby, G. C., Jr.↗
Prediction of unsteady aerodynamic loadings caused by trailing edge control surface motions in subsonic compressible flow: Analysis and results
A theoretical analysis and a computer program have been developed for the prediction of unsteady lifting surface loadings caused by motions of trailing edge control surfaces having sealed gaps. The final form of the downwash integral equation has been formulated by isolating the singularities from the non-singular terms and establishing a preferred solution process to remove and evaluate the downwash discontinuities in a systematic manner. Comparisons of theoretical and experimental pressure data are made for several control surface configurations. The comparisons indicate that reasonably accurate theoretical pressure distributions and generalized forces may be obtained for a wide variety of control surface configurations. Spanwise symmetry or antisymmetry of motion, and up to four control surfaces on each half span can be accommodated.
Rowe, W. S.↗