Latest content added for UNT Digital Library Partner: UNT Libraries Government Documents Departmenthttp://digital.library.unt.edu/explore/partners/UNTGD/browse/?fq=untl_collection:NACA&fq=str_title_serial:NACA+Research+Memorandums2014-09-25T20:32:43-05:00UNT LibrariesThis is a custom feed for browsing UNT Digital Library Partner: UNT Libraries Government Documents DepartmentAverage Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc100824/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc100824/"><img alt="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" title="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" src="http://digital.library.unt.edu/ark:/67531/metadc100824/thumbnail/"/></a></p><p>Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.</p>Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279644/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279644/"><img alt="Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data" title="Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data" src="http://digital.library.unt.edu/ark:/67531/metadc279644/thumbnail/"/></a></p><p>None</p>The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279634/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279634/"><img alt="The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow" title="The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow" src="http://digital.library.unt.edu/ark:/67531/metadc279634/thumbnail/"/></a></p><p>None</p>An experimental study of five annular air inlet configurations at subsonic and transonic speeds2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279680/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279680/"><img alt="An experimental study of five annular air inlet configurations at subsonic and transonic speeds" title="An experimental study of five annular air inlet configurations at subsonic and transonic speeds" src="http://digital.library.unt.edu/ark:/67531/metadc279680/thumbnail/"/></a></p><p>None</p>Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279650/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279650/"><img alt="Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds" title="Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds" src="http://digital.library.unt.edu/ark:/67531/metadc279650/thumbnail/"/></a></p><p>None</p>Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.262014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279664/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279664/"><img alt="Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26" title="Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26" src="http://digital.library.unt.edu/ark:/67531/metadc279664/thumbnail/"/></a></p><p>None</p>A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279629/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279629/"><img alt="A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel" title="A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel" src="http://digital.library.unt.edu/ark:/67531/metadc279629/thumbnail/"/></a></p><p>None</p>A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279618/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279618/"><img alt="A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees" title="A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees" src="http://digital.library.unt.edu/ark:/67531/metadc279618/thumbnail/"/></a></p><p>None</p>Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279567/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279567/"><img alt="Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel" title="Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel" src="http://digital.library.unt.edu/ark:/67531/metadc279567/thumbnail/"/></a></p><p>None</p>Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings2014-03-30T18:00:15-05:00http://digital.library.unt.edu/ark:/67531/metadc279554/<p><a href="http://digital.library.unt.edu/ark:/67531/metadc279554/"><img alt="Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings" title="Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings" src="http://digital.library.unt.edu/ark:/67531/metadc279554/thumbnail/"/></a></p><p>None</p>