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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 0 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 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 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 Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 by : P. Calvin Stainback
Download or read book Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 written by P. Calvin Stainback and published by . This book was released on 1962 with total page 28 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 Pressure Measurements on Two 60 Degree Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degree and 45 Degrees at a Mach Number of 4.95 by : P. CALVIN. STAINBACK
Download or read book Pressure Measurements on Two 60 Degree Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degree and 45 Degrees at a Mach Number of 4.95 written by P. CALVIN. STAINBACK and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to measure the pressures on two 60 degree swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0 and 45 degrees. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was 15.19 x 10 to the 6th power and the angle of attack was varied from 0 to 20 degrees. The results of the investigation indicated that, in general, Newtonian theory would not predict the pressure distri ution on the model in a plane normal to the leading edge for angles of attac greater than zero. A method which utilizes a linear combination of viscous and inviscid pressure terms, developed by Creager for predicting pressures on blunt-leading-e ge delta wing at angles of attac, was in good agreement with the measured pressure distributions. The stagnationline pressure level could be predicted within!9 percent by using the ideal-gas normal-shock relationship with the normal component of the free-stream Mach number. (Author).
Book Synopsis Heat-transfer and Pressure Distributions of a 60 Deg Delta Wing with Dihedral at a Mach Number of 6 and Angles of Attack from 0 Deg to 52 Deg by :
Download or read book Heat-transfer and Pressure Distributions of a 60 Deg Delta Wing with Dihedral at a Mach Number of 6 and Angles of Attack from 0 Deg to 52 Deg written by and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure 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 Pressure 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 30 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 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 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 by : Peter T. Bernot
Download or read book Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Distributions of a 60 Swept Delta Wing with Dihedral at a Mach Number of 6 and Angles of Attack from 0 to 52 by : Robert A. Jones
Download or read book Heat Transfer and Pressure Distributions of a 60 Swept Delta Wing with Dihedral at a Mach Number of 6 and Angles of Attack from 0 to 52 written by Robert A. Jones and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers by : William M. Murray (Jr.)
Download or read book Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers written by William M. Murray (Jr.) and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 by : Philip E. Everhart
Download or read book Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 written by Philip E. Everhart and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer distributions were obtained on 700 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°.
