Download or read book Effects of Corner Radius on Stagnation point Velocity Gradients on Blunt Axisymmetric Bodies written by Ernest V. Zoby and published by . This book was released on 1965 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Corner Radius on Stagnation point Velocity Gradients on Blunt Axisymmetric Bodies written by and published by . This book was released on 1965 with total page 28 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 1972 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Natural Chemical Impurities and Crystallite Orientation on the Erosion Behavior of Artificial Graphite written by Howard G. Maahs and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Char Formation and Surface Recession of a Composite Ablation Material with a Silicone resin Base written by Allen G. McLain and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A composite ablation material containing a silicone- resin base, silica fibers, and phenolic and silica hollow microspheres has been subjected to a wide range of test conditions to study its charring behavior. The ablation tests were performed at stagnationpoint pressures ranging from 0.016 to 1.3 atm and heating rates ranging from 1.34 MW/m2 to 14.8 MW/m2 in air and nitrogen. The resulting char-layer surfaces fell into three categories - black char, glassy-coated char, and gray char - as heating rates (and char surface temperatures) were increased. The char layers formed contained large percentages by weight of silicon dioxide. Silicon carbide was found to be in chars formed at high heating rates. Empirical correlations of surface recession were determined. For the higher heating rates where steady-state ablation was approached, char-layer constituents and mass loss could be predicted adequately with chemical equilibrium in the reactions at the surface assumed.

Download or read book Approximate Relations for Laminar Heat transfer and Shear stress Functions in Equilibrium Dissociated Air written by Ernest V. Zoby and published by . This book was released on 1968 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Manned Operations for the Apollo Lunar Module in a Simulated Space Environment written by O. L. Pearson and published by . This book was released on 1970 with total page 920 pages. Available in PDF, EPUB and Kindle. Book excerpt: Simulated space environment performance tests of Apollo lunar module in thermal vacuum environment.

Download or read book Simulation in Ground test Facilities of Ablation Performance of Charring Ablators During Atmospheric Entry written by Stephen Stern Tompkins and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Optimum Shape for Transpiration cooled Nosetip of a Re entry Vehicle written by Kevin E. Yelmgren and published by . This book was released on 1978 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: The variations of parameters method was used to determine the optimum nose shape for a reentry vehicle having a transpiration-cooled nosetip (TCNT). Three families of nose shapes were considered - The oblate ellipsoid, the flat face - round shoulder, and the spherical arc - round shoulder. These families are bounded by the flat face - sharp corner at one extreme and the hemisphere at the other extreme. The amount of coolant required by each nose shape during reentry was determined by using a high speed computer to couple the aerodynamic equations with the trajectory equations. The optimum shape is the shape which requires the least amount of coolant for reentry. The flat face - sharp corner shape was found to require the least amount of coolant, about 60 percent less water than the hemisphere. Although the time to impact is longer for the flat face, the smaller surface area and lower heating intensity more than offsets the increased reentry time. The possibility of an optimum flat face height was also investigated; no face height was found that minimized the total heating to the vehicle during reentry. (Author).

Download or read book Descriptions and Operating Parameters of a Mach 2 Nozzle System for the Langley 11 inch Ceramic heated Tunnel written by Kenneth Sutton and published by . This book was released on 1968 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1966-12 with total page 1288 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1967 with total page 2300 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Investigation of Ablation Behavior of Avcoat 5026 39M Over a Wide Range of Thermal Environments written by Roger K. Crouch and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1969 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight and Ground test Evaluation of Pyrrone Foams written by Allen G. McLain and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two Pyrrone materials, pure Pyrrone foam with a density of 481 kg/cu m and hollow glass microsphere-Pyrrone composite with a density of 962 kg/cu m, were tested in the Langley 20-inch hypersonic arc heated tunnel at pressure levels from 0.06 to 0.27 atm and heating rates from 1.14 to 11.4 MW/sq m. The 481-kg/cu m Pyrrone foam was also flight tested as an experiment aboard a Pacemaker test vehicle. The results of the ground tests indicated that the thermal effectiveness of the 481-kg/cu m Pyrrone foam was superior to the 962-kg/cu m glass sphere-Pyrrone composite. The 481-kg/cu m Pyrrone foam had approximately one-half the thermal effectiveness of low density phenolic nylon. The 481-kg/cu m Pyrrone foam experienced random mechanical char removal over the entire range of test conditions. Char thermal property inputs for an ablation computer program were developed from the ground test data of the 481-kg/cu m Pyrrone foam. The computer program using these developed char thermal properties, as well as the measured uncharred material properties, adequately predicted the in-depth temperature histories measured during the Pacemaker flight.

Download or read book Experimental Stagnation point Velocity Gradients and Heat transfer Coefficients for a Family of Blunt Bodies at Mach 8 and Angles of Attack written by James C. Ellison and published by . This book was released on 1969 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Conceptual Shape Optimization of Entry Vehicles written by Dominic Dirkx and published by Springer. This book was released on 2016-12-09 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book covers the parameterization of entry capsules, including Apollo capsules and planetary probes, and winged entry vehicles such as the Space Shuttle and lifting bodies. The aerodynamic modelling is based on a variety of panel methods that take shadowing into account, and it has been validated with flight and wind tunnel data of Apollo and the Space Shuttle. The shape optimization is combined with constrained trajectory analysis, and the multi-objective approach provides the engineer with a Pareto front of optimal shapes. The method detailed in Conceptual Shape Optimization of Entry Vehicles is straightforward, and the output gives the engineer insight in the effect of shape variations on trajectory performance. All applied models and algorithms used are explained in detail, allowing for reconstructing the design tool to the researcher’s requirements. Conceptual Shape Optimization of Entry Vehicles will be of interest to both researchers and graduate students in the field of aerospace engineering, and to practitioners within the aerospace industry.