Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Transition Of The Laminar Boundary Layer On A Delta Wing With 74 Degree Sweep In Free Flight At Mach Numbers From 28 To 53
Download Transition Of The Laminar Boundary Layer On A Delta Wing With 74 Degree Sweep In Free Flight At Mach Numbers From 28 To 53 full books in PDF, epub, and Kindle. Read online Transition Of The Laminar Boundary Layer On A Delta Wing With 74 Degree Sweep In Free Flight At Mach Numbers From 28 To 53 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Transition of the Laminar Boundary Layer on a Delta Wing with 74 Degree Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 by : Gary T. Chapman
Download or read book Transition of the Laminar Boundary Layer on a Delta Wing with 74 Degree Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 written by Gary T. Chapman and published by . This book was released on 1961 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transition of the Laminar Boundary Layer on a Delta Wing with 74 Degree Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 by : GARY T. CHAPMAN
Download or read book Transition of the Laminar Boundary Layer on a Delta Wing with 74 Degree Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 written by GARY T. CHAPMAN and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio, AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. (Author).
Book Synopsis Transition of the Laminar Boundary Layer on a Delta Wing with 74° Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 by : Gary T. Chapman
Download or read book Transition of the Laminar Boundary Layer on a Delta Wing with 74° Sweep in Free Flight at Mach Numbers from 2.8 to 5.3 written by Gary T. Chapman and published by . This book was released on 1961 with total page 42 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 1974 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 by : S. R. Pate
Download or read book Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 written by S. R. Pate and published by . This book was released on 1963 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.
Book Synopsis Analysis of Boundary-layer Transition on X-15-2 Research Airplane by : Albert L. Braslow
Download or read book Analysis of Boundary-layer Transition on X-15-2 Research Airplane written by Albert L. Braslow and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 by : Samuel Ralph Pate
Download or read book Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 written by Samuel Ralph Pate and published by . This book was released on 1965 with total page 95 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 36.75 and 45 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and From 2.50 to 4.05 by :
Download or read book Heat Transfer to 36.75 and 45 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and From 2.50 to 4.05 written by and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Sweep on In-flight Boundary-layer Transition for a Laminar Flow Wing at Mach Numbers from 0.60 to 0.79 by : Bianca Trujillo Anderson
Download or read book Effects of Wing Sweep on In-flight Boundary-layer Transition for a Laminar Flow Wing at Mach Numbers from 0.60 to 0.79 written by Bianca Trujillo Anderson and published by . This book was released on 1990 with total page 0 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 Flight-measured Laminar Boundary Layer Transition Phenomena Including Stability Theory Analysis by : Clifford J. Obara
Download or read book Flight-measured Laminar Boundary Layer Transition Phenomena Including Stability Theory Analysis written by Clifford J. Obara and published by . This book was released on 1985 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressures and Heat Transfer on a 75 ̊swept Delta Wing with Trailing-edge Flap at Mach 6 and Angles of Attack to 90 by : J. Wayne Keyes
Download or read book Pressures and Heat Transfer on a 75 ̊swept Delta Wing with Trailing-edge Flap at Mach 6 and Angles of Attack to 90 written by J. Wayne Keyes and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure and heat transfer on swept delta wing with trailing-edge flap.
Book Synopsis Summary of Laminar Boundary Layer Control Research by : Northrop Corporation Boundary Layer Research Section
Download or read book Summary of Laminar Boundary Layer Control Research written by Northrop Corporation Boundary Layer Research Section and published by . This book was released on 1964 with total page 432 pages. Available in PDF, EPUB and Kindle. Book excerpt: At subsonic speeds, full length laminar flow and low drags were obtained up to high length Reynolds numbers on a thin straight, on a swept laminar suction wing and on a suction body of revolution. Moderately increased suction rates in the most critical region of a straight and a swept laminar suction wing enabled full chord laminar flow in the presence of external sound. Theoretical investigatiions are concerned with nonlinear boundary layer oscillations and stability investigations (assuming small disturbances) of a supersonic laminar boundary layer on a flat plate up to high supersonic speeds as well as on a highly swept supersonic low drag suction wing of low wave drag. On a supersonic flat laminar suction plate with and without weak incident shock waves, extensive laminar flow and low equivalent drags were obtained at M = 3 up to length Reynolds numbers of 26 x 1000000. Further supersonic low drag suction experiments on a suction body of revolution, on a 36 degree supersonic yawing wing, as well as on a 72 degree supersonic yawing wing (swept behind the Mach cone) of low wave drag, are described. The latter wing showed full chord laminar flow with a subsonic type pressure distribution at M = 2 and R sub C approximately equal to 1000000. (Author).
Book Synopsis Maintaining Laminar Flow in the Boundary Layer Using a Swept-back Wing by :
Download or read book Maintaining Laminar Flow in the Boundary Layer Using a Swept-back Wing written by and published by . This book was released on 1948 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: (2) Backward shift of the transition point.
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 Flight-measured Laminar Boundary-layer Transition Phenomena Including Stability Theory Analysis by : Clifford J. Obara
Download or read book Flight-measured Laminar Boundary-layer Transition Phenomena Including Stability Theory Analysis written by Clifford J. Obara and published by . This book was released on 1985 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
