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 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 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.
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:
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:
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:
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:
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:
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 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).
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:
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:
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 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 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:
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:
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:
