Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Static Force Tests At Mach 8 Of Sharp And Blunt 20 Deg Half Angle Cones With A Blunt 70 Deg Swept Delta Wing
Download Static Force Tests At Mach 8 Of Sharp And Blunt 20 Deg Half Angle Cones With A Blunt 70 Deg Swept Delta Wing full books in PDF, epub, and Kindle. Read online Static Force Tests At Mach 8 Of Sharp And Blunt 20 Deg Half Angle Cones With A Blunt 70 Deg Swept Delta Wing ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Static Force Tests at Mach 8 of Sharp and Blunt 20-deg Half-angle Cones with a Blunt 70-deg Swept Delta Wing by : G. H. Merz
Download or read book Static Force Tests at Mach 8 of Sharp and Blunt 20-deg Half-angle Cones with a Blunt 70-deg Swept Delta Wing written by G. H. Merz and published by . This book was released on 1962 with total page 26 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 1965 with total page 390 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Collection of Technical Papers by :
Download or read book A Collection of Technical Papers written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Force and Moment Characteristics of Spheres and Cones at Mach 7.0 in Methane-air Combustion Products by : L. Roane Hunt
Download or read book Aerodynamic Force and Moment Characteristics of Spheres and Cones at Mach 7.0 in Methane-air Combustion Products written by L. Roane Hunt and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Compilation of Longitudinal Aerodynamic Characteristics Including Pressure Information for Sharp-and Blunt-nose Cones Having Flat and Modified Bases by : Sandia Corporation
Download or read book A Compilation of Longitudinal Aerodynamic Characteristics Including Pressure Information for Sharp-and Blunt-nose Cones Having Flat and Modified Bases written by Sandia Corporation and published by . This book was released on 1965 with total page 596 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 1056 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow by : Max Kinslow
Download or read book Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow written by Max Kinslow and published by . This book was released on 1974 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
Book Synopsis Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 by : J. S. Hahn
Download or read book Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 written by J. S. Hahn and published by . This book was released on 1972 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0 by :
Download or read book Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0 written by and published by . This book was released on 1961 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of High-speed, Convective, Heat-transfer Computation Methods by : Michael E. Tauber
Download or read book A Review of High-speed, Convective, Heat-transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Measurement of Drag and Static Stability for a Blunt-nosed 10° Half-angle Cone at Mach Number 15 by : Dale L. Compton
Download or read book Free-flight Measurement of Drag and Static Stability for a Blunt-nosed 10° Half-angle Cone at Mach Number 15 written by Dale L. Compton and published by . This book was released on 1961 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies by : James E. Brunk
Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
Book Synopsis The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° by : John B. McDevitt
Download or read book The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° written by John B. McDevitt and published by . This book was released on 1960 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Convective Heat Transfer in Planetary Gases by : Joseph G. Marvin
Download or read book Convective Heat Transfer in Planetary Gases written by Joseph G. Marvin and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Equilibrium convective heat transfer in several real gases was investigated. The gases considered were air, nitrogen, hydrogen, carbon dioxide, and argon. Solutions to the similar form of the boundary-layer equations were obtained for flight velocities to 30,000 ft/sec for a range of parameters sufficient to define the effects of pressure level, pressure gradient, boundary-layer-edge velocity, and wall temperature. Results are presented for stagnation-point heating and for the heating-rate distribution. For the range of parameters investigated the wall heat transfer depended on the transport properties near the wall and precise evaluation of properties in the high-energy portions of the boundary layer was not needed. A correlation of the solutions to the boundary-layer equations was obtained which depended only on the low temperature properties of the gases. This result can be used to evaluate the heat transfer in gases other than those considered. The largest stagnation-point heat transfer at a constant flight velocity was obtained for argon followed successively by carbon dioxide, air, nitrogen, and hydrogen. The blunt-body heating-rate distribution was found to depend mainly on the inviscid flow field. For each gas, correlation equations of boundary-layer thermodynamic and transport properties as a function of enthalpy are given for a wide range of pressures to a maximum enthalpy of 18,000 Btu/lb.
Book Synopsis Heat-Transfer Measurements on the Apexes of Two 60 Deg Sweptback Delta Wings (Panel Semiapex Angle of 30 Deg) Having 0 Deg and 45 Deg Dihedral at a Mach Number of 4.95 by :
Download or read book Heat-Transfer Measurements on the Apexes of Two 60 Deg Sweptback Delta Wings (Panel Semiapex Angle of 30 Deg) Having 0 Deg and 45 Deg Dihedral at a Mach Number of 4.95 written by and published by . This book was released on 1961 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to evaluate the heat-transfer rates at the apex of two 60 degree sweptback delta wings (panel semi-apex angle of 30 degrees) having cylindrical leading edges and 0 degrees and 45 degree positive dihedral. The models tested might correspond to the first several feet of a hypersonic reentry vehicle. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. nominal test-section unit Reynolds numbers varied from 2 x 10(exp 6) to 12 x 10(exp 6) per foot. The results of the investigation indicated that the laminar heat-transfer distributions (ratio of local to stagnation-line heating rate) about the models normal to the leading edges were in close agreement with two-dimensional blunt-body theory. The three-dimensional stagnation point heat-transfer rate on the 0 degree dihedral model was in excellent agreement with theory and the stagnation-line heat transfer on the straight portion of the leading edge of both models approached a constant level 12 percent above the theoretical stagnation-line level on an isolated swept infinite cylinder. When the heating rates on the 45 degree dihedral model (planform sweep of 69.3 degree) were compared with those on the 0 degree dihedral model (planform sweep of 60 degrees) at equal angles of attack and equal lifts greater than zero, the stagnation-line heating rates on the 45 degrees dihedral model were, in general, considerably lower as a result of the difference in effective sweeps of the leading edges. On the wing panels inboard from the stagnation lines, the differences in heating were very small. The stagnation-line heat-transfer variation with angle of attack, the shift in stagnation-line location, and the reduction in stagnation-line heat transfer resulting from the increase in effective sweep when positive dihedral is incorporated into a constant-panel 0 degree dihedral wing, all agreed with the results of a theoretical study made of highly swept delta.
Book Synopsis Experimental Determination of Aerodynamic Drag on a Blunted 10-deg Cone at Angles of Attack in Hypersonic, Rarefied Flow by : David E. Boylan
Download or read book Experimental Determination of Aerodynamic Drag on a Blunted 10-deg Cone at Angles of Attack in Hypersonic, Rarefied Flow written by David E. Boylan and published by . This book was released on 1964 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL WING AND BLUNT-BODY SHAPES APPLICABLE FOR USE AS REENTRY CONFIGURATIONS AT A MACH NUMBER OF 6.8 AND ANGLES OF ATTACK UP TO 90 DEG by :
Download or read book STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL WING AND BLUNT-BODY SHAPES APPLICABLE FOR USE AS REENTRY CONFIGURATIONS AT A MACH NUMBER OF 6.8 AND ANGLES OF ATTACK UP TO 90 DEG written by and published by . This book was released on 1959 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
