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Investigation Of Heat Transfer On A Simulated 82 Deg Swept Delta Wing In Free Flight At Angle Of Attack At Mach Numbers Up To 98
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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 Investigation of Heat Transfer on a Simulated 82 Swept Delta Wing in Free Flight at Angle of Attack at Mach Numbers Up to 9.8 by : John F. Jr Royall
Download or read book Investigation of Heat Transfer on a Simulated 82 Swept Delta Wing in Free Flight at Angle of Attack at Mach Numbers Up to 9.8 written by John F. Jr Royall and published by . This book was released on 1962 with total page 36 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 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 Investigation of Heat Transfer and Pressures on Highly Swept Flat and Dihedraled Delta Wings at Mach Numbers of 6.8 and 9.6 and Angles of Attack to 90 Degrees by : James C. Dunavant
Download or read book Investigation of Heat Transfer and Pressures on Highly Swept Flat and Dihedraled Delta Wings at Mach Numbers of 6.8 and 9.6 and Angles of Attack to 90 Degrees written by James C. Dunavant and published by . This book was released on 1962 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Measurements of Heat Transfer to a Simulated Winged Cone Glide Vehicle at Angles of Attack and at Mach Numbers from 10 to 14.3 by : James R. Hall
Download or read book Free Flight Measurements of Heat Transfer to a Simulated Winged Cone Glide Vehicle at Angles of Attack and at Mach Numbers from 10 to 14.3 written by James R. Hall and published by . This book was released on 1961 with total page 48 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°.
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 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 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 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 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 Measurement of Aerodynamic Heat Transfer to a Deflected Trailing-edge Flap on a Delta Fin in Free Flight at Mach Numbers from 1.5 to 2.6 by : Leo T. Chauvin
Download or read book Measurement of Aerodynamic Heat Transfer to a Deflected Trailing-edge Flap on a Delta Fin in Free Flight at Mach Numbers from 1.5 to 2.6 written by Leo T. Chauvin and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-Transfer Investigation of Langley Research Center Delta Wing Configurations at Mach Numbers 8 and 10.5 by :
Download or read book Heat-Transfer Investigation of Langley Research Center Delta Wing Configurations at Mach Numbers 8 and 10.5 written by and published by . This book was released on 1973 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer tests for two simple delta wing configurations submitted by NASA-Langley Research Center were conducted at Mach numbers 8 and 10.5. Test conditions provided both Mach number and Reynolds number simulation for typical lifting body reentry trajectories. This report presents the major test results and comparisons with theoretical calculations. Specific test results include heat-transfer distributions, shock angles, limited pressure measurements, and boundary-layer transition results.
Book Synopsis NASA Scientific and Technical Publications by :
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1987 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° by : John B. McDevitt
Download or read book The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° written by John B. McDevitt and published by . This book was released on 1960 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
