Investigation At Mach Numbers From 080 To 143 Of Pressure And Load Distributions Over A Thin 45c Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Investigation At Mach Numbers From 080 To 143 Of Pressure And Load Distributions Over A Thin 45c Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies PDF full book. Access full book title Investigation At Mach Numbers From 080 To 143 Of Pressure And Load Distributions Over A Thin 45c Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies.
Author | : Thomas L. Fischetti |
Publisher | : |
Total Pages | : 98 |
Release | : 1957 |
Genre | : Aerodynamic load |
ISBN | : |
Download Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45© Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies Book in PDF, ePub and Kindle
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.
Author | : Thomas L. Fischetti |
Publisher | : |
Total Pages | : 94 |
Release | : 1957 |
Genre | : Aerodynamic load |
ISBN | : |
Download Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45 Degree Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies Book in PDF, ePub and Kindle
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.
Author | : |
Publisher | : |
Total Pages | : 82 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations Book in PDF, ePub and Kindle
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Author | : Donald L. Loving |
Publisher | : |
Total Pages | : 92 |
Release | : 1961 |
Genre | : Aerodynamics |
ISBN | : |
Download A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance Book in PDF, ePub and Kindle
Author | : John P. Jr Mugler |
Publisher | : |
Total Pages | : 78 |
Release | : 1960 |
Genre | : Wall pressure (Aerodynamics) |
ISBN | : |
Download Basic Pressure Measurements at a Mach Number of 1/43 on a Thing 45 Degree Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations Book in PDF, ePub and Kindle
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.
Author | : John P. Mugler |
Publisher | : |
Total Pages | : 79 |
Release | : 1957 |
Genre | : Aerodynamic load |
ISBN | : |
Download Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low-aspect-ratio Delta Wing in Combination with Basic and Indented Bodies Book in PDF, ePub and Kindle
Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.
Author | : W. F. Lindsey |
Publisher | : |
Total Pages | : 24 |
Release | : 1954 |
Genre | : Aerodynamics |
ISBN | : |
Download The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 Book in PDF, ePub and Kindle
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Author | : Marvin Kussoy |
Publisher | : |
Total Pages | : 32 |
Release | : 1962 |
Genre | : Mach number |
ISBN | : |
Download 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 Book in PDF, ePub and Kindle
Author | : George H. Holdaway |
Publisher | : |
Total Pages | : 82 |
Release | : 1960 |
Genre | : Aerodynamics |
ISBN | : |
Download Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms Book in PDF, ePub and Kindle
Author | : George H. Holdaway |
Publisher | : |
Total Pages | : 62 |
Release | : 1959 |
Genre | : Airplanes |
ISBN | : |
Download Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number Book in PDF, ePub and Kindle