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°.
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°.
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:
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:
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 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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.
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:
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:
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:
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3 4 and 4 7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 to 45 written by Robert L. Stallings and published by . This book was released on 1964 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Pressure Distributions on a Flat plate Delta Wing Swept 65 Deg at a Mach Number of 5 97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack written by and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Experimental Pressure and Heat Transfer Distributions on Blunt nose Delta Wings for Angles of Attack Up to 30 at Mach Number 7 written by R. Douglas Archer and published by . This book was released on 1963 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
