Download or read book Experimental Investigation of Metal Temperatures of Air cooled Airfoil Leading Edges at Subsonic Flow and Gas Temperatures Up to 2780 Degrees F written by Francis S. Stepka and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Metal Temperatures of Air cooled Airfoil Leading Edges at Subsonic Flow and Gas Temperatures Up to 2780 Deg F written by and published by . This book was released on 1959 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Metal Temperatures of Air cooled Airfoil Leading Edges at Subsonic Flow and Gas Temperatures Up to 2780 Degrees F written by Francis S. Stepka and published by . This book was released on 1959 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Metal Temperatures of Air cooled Airfoil Leading Edges at at Subsonic Flow and Gas Temperatures Up to 2780 F written by Francis S. Stepka and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Thermal buckling Characteristics of Flanged Thin shell Leading Edges written by Jerald M. Jenkins and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The leading edges of winged hypersonic aircraft are known to be subjected to intense aerodynamic heating (ref. 1) in flight. Detailed research investigations into specific types of leading edges suitable for hypersonic use have been limited. The heat-sink concept, although excessive in weight and limited to short durations of heating (ref. 2), has been the most widely used type of leading edge for hypersonic application. Limited experimental and analytical work on shell types of leading edges (refs. 3 and 4) has been conducted; however, the thermal-buckling behavior of leading edges has been defined only in analytical studies, such as references 5 and 6. These theories include simplifying assumptions, which impose limitations on their applicability to design problems. A series of experimental investigations into the thermal-buckling behavior of flanged, thin-shell leading edges has been conducted at the NASA Flight Research Center, Edwards, Calif.

Download or read book Procedure for Scaling of Experimental Turbine Vane Airfoil Temperatures from Low to High Gas Temperatures written by Herbert J. Gladden and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Development of procedure for scaling of experimental turbine vane airfoil temperatures from low to high gas temperatures.

Download or read book Metal Temperatures and Coolant Flow in a Wire cloth Transpiration cooled Turbine Vane written by Herbert J. Gladden and published by . This book was released on 1975 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Analysis of the Effects on Life of Leading edge Holes in an Airfoil Subjected to Arbitrary Spanwise and Chordwise Temperature Distributions written by Albert Kaufman and published by . This book was released on 1975 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Heat Transfer and Flow Characteristics in Various Geometries of 2 pass Internal Cooling Passages of Gas Turbine Airfoils written by Denis Chanteloup and published by . This book was released on 2002 with total page 181 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight Measurements of Airplane Structural Temperatures at Supersonic Speeds written by Richard D. Banner and published by . This book was released on 1957 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Skin and structural temperatures have been obtained on the X-1B and X-1E research airplanes under transient aerodynamic heating conditions at speeds up to Mach numbers near 2.0. Extensive temperature measurements were obtained throughout the X-1B airplane, and temperature distributions are shown on the nose cone, the wing, and the vertical tail. Temperatures for the X-1E wing leading edge and internal wing structure were compared with similar data for the X-1B. No critical skin and structural temperatures were obtained on the two airplanes over the range of these tests. Simplified calculations of the skin temperatures in the laminar-flow regions of the nose cone and the leading edges agreed favorably with the general trends in the measured data. The flat-plate skin-temperature calculations in the turbulent-flow regions agreed favorably with the measured data on the nose cone and at the midsemispan station of the wing but overestimated the vertical-tail skin temperatures and also the upper wing skin temperature near the wing tip. The relatively low values of the upper skin temperatures that were measured at the wing tip were believed to be caused by separated-flow effects in this region.

Download or read book A Feasibility Study of Heat pipe cooled Leading Edges for Hypersonic Cruise Aircraft written by Calvin C. Silverstein and published by . This book was released on 1971 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transient Temperature Distribution in an Aerodynamically Heated Multiweb Wing written by George E. Griffith and published by . This book was released on 1953 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation Into the Temperature Profile of a Compliant Foil Air Bearing written by Kevin Radil and published by BiblioGov. This book was released on 2013-07 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.

Download or read book Analysis of Metal Temperature and Coolant Flow with a Thermal barrier Coating on a Full coverage film cooled Turbine Vane written by Peter L. Meitner and published by . This book was released on 1978 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurements of Aerodynamic Heating Obtained During Demonstration Flight Tests of the Douglas D 558 II Airplane written by Ira P. Jones and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Investigation of High Temperature Leading Edge Cooling Using Metallic Foam written by Matthew Sheridan and published by . This book was released on 2006 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experiment to simulate the realistic surface temperature profile of a wing at supersonic conditions with heating at the wing's leading edge. The optimal design that minimizes the thermal resistance and pumping power is the 20 pore per inch (PPI) metal foam wing at 15 standard cubic feet per minute (scfm).

Download or read book Free flight Measurements of Aerodynamic Heat Transfer to Mach Number 3 9 and of Drag to Mach Number 6 9 of a Fin stabilized Cone cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.