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Heat Transfer Measurements At A Mach Number Of 495 On Two 60 Degree Sweot Delta Wings With Blunt Leading Edges And Dihedral Angles Of 0 Degrees And 46 Degrees
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Book Synopsis Heat-transfer Measurements at a Mach Number of 4.95 on Two 60 Degree Sweot Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degrees and 46 Degrees by : P. Calvin Stainback
Download or read book Heat-transfer Measurements at a Mach Number of 4.95 on Two 60 Degree Sweot Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degrees and 46 Degrees written by P. Calvin Stainback and published by . This book was released on 1961 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements at a Mach Number of 4.95 on Two 60 Degree Sweot Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degrees and 46 Degrees by : P. Calvin Stainback
Download or read book Heat-transfer Measurements at a Mach Number of 4.95 on Two 60 Degree Sweot Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degrees and 46 Degrees written by P. Calvin Stainback and published by . This book was released on 1961 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Heat-Transfer Measurements at a Mach Number of 4.95 on Two 60 Deg Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Deg and 45 Deg by : P. Calvin Stainback
Download or read book Heat-Transfer Measurements at a Mach Number of 4.95 on Two 60 Deg Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Deg and 45 Deg written by P. Calvin Stainback and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements at a Mach Number of 4.95 on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° by : P. Calvin Stainback
Download or read book Heat-transfer Measurements at a Mach Number of 4.95 on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° written by P. Calvin Stainback and published by . This book was released on 1961 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on the Apexes of Two 60 Degree Sweptback Dekta Wings (panel Semiapex Angle of 30 Degrees) Having 0 Degrees and 45 Degrees Dihedral at a Mach Number of 4.95 by : Charles R. Gunn
Download or read book Heat-transfer Measurements on the Apexes of Two 60 Degree Sweptback Dekta Wings (panel Semiapex Angle of 30 Degrees) Having 0 Degrees and 45 Degrees Dihedral at a Mach Number of 4.95 written by Charles R. Gunn and published by . This book was released on 1961 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by :
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on the Apexes of Two 60° Sweptback Delta Wings (panel Semiapex Angle of 30°) Having 0° and 45° Dihedral at a Mach Number of 4.95 by : Charles R. Gunn
Download or read book Heat-transfer Measurements on the Apexes of Two 60° Sweptback Delta Wings (panel Semiapex Angle of 30°) Having 0° and 45° Dihedral at a Mach Number of 4.95 written by Charles R. Gunn and published by . This book was released on 1961 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow by : Mitchel H. Bertram
Download or read book An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Book Synopsis Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 and 8 data for expansion corner flows by : Louis G. Kaufman
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 and 8 data for expansion corner flows written by Louis G. Kaufman and published by . This book was released on 1963 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.
Book Synopsis A Visual Technique for Determining Qualitative Aerodynamic Heating Rates on Complex Configurations by : P. Calvin Stainback
Download or read book A Visual Technique for Determining Qualitative Aerodynamic Heating Rates on Complex Configurations written by P. Calvin Stainback and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: "An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation temperature of 400 degrees F to evaluate a visual technique for obtaining qualitative aerodynamic heat-transfer data on complex configurations. This technique utilized a temperature-sensitive paint which exhibited the characteristic that a pronounced color change occurred at a known temperature. The visual results obtained with the temperature-sensitive paint indicated that this technique was satisfactory for determining qualitative heat-transfer rates on various bodies, some of which exhibited complex flow patterns. The results obtained have been found useful to guide the instrumentation of quantitative heat-transfer models, to supplement quantitative heat-transfer measurements, and to make preliminary heat-transfer studies for new configurations."p.[1].
Book Synopsis Heat-transfer and Pressure Measurements on Delta Wings at Mach Numbers of 3.51 and 4.65 and Angles of Attack from -45 Degrees to 45 Degrees by : United States. National Aeronautics and Space Administration
Download or read book Heat-transfer and Pressure Measurements on Delta Wings at Mach Numbers of 3.51 and 4.65 and Angles of Attack from -45 Degrees to 45 Degrees written by United States. National Aeronautics and Space Administration and published by . This book was released on 1964 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Heat Transfer on a Simulated 82 Deg Swept Delta Wing in Free Flight at Angle of Attack at Mach Numbers Up to 9.8 by :
Download or read book Investigation of Heat Transfer on a Simulated 82 Deg Swept Delta Wing in Free Flight at Angle of Attack at Mach Numbers Up to 9.8 written by and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer on the Lifting Surfaces of a 60 Degree Delta Wing at Angle of Attack for Mach Number 1.98 by : Howard S. Carter
Download or read book Heat Transfer on the Lifting Surfaces of a 60 Degree Delta Wing at Angle of Attack for Mach Number 1.98 written by Howard S. Carter and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The heat transfer and pressures on the lifting surfaces of a 60 degree delta wing with NACA 65A005 profile are presented for angles of attack up to 9 degrees. The tests were made under steady flow conditions in a free jet at a Mach number of 1.98 and for a Reynolds number based on the mean aerodynamic chord of 22,000,000.
Book Synopsis Heat-transfer Measurements at a Mach Number of 8 in the Vicinity of a 90 [degrees] Interior Corner Alined with the Free-stream Velocity by : P. Calvin Stainback
Download or read book Heat-transfer Measurements at a Mach Number of 8 in the Vicinity of a 90 [degrees] Interior Corner Alined with the Free-stream Velocity written by P. Calvin Stainback and published by . This book was released on 1964 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Distribution on 70°swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 90° by : Philip E. Everhart
Download or read book Heat-transfer Distribution on 70°swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 90° written by Philip E. Everhart and published by . This book was released on 1964 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer distributions were obtained on 70° swept slab delta wings with sharp and blunt noses and cylindrical leading edges. The free-stream Reynolds number based on model thickness was 9 x 10(4). Lees' theory for the heat-transfer distribution is shown to be in good agreement with the data obtained on the nose and leading edge. The point of peak heating on the leading edge is in close agreement with the Newtonian stagnation point at all angles of attack. At angles of attack from 40° to 60° cross-flow theory was in excellent agreement with experimental center-line data; however, at other model attitudes the theory differed significantly from experiment. Nose blunting resulted in reduced heating rates over the aft center-line section of the wing at angles of attack less than about 40°.
Book Synopsis Heat-transfer Distribution on 70 Degrees Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 90 Degrees by : Philip E. Everhart
Download or read book Heat-transfer Distribution on 70 Degrees Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 90 Degrees written by Philip E. Everhart and published by . This book was released on 1964 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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