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BOOK EXCERPT:
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Product Details :
Genre |
: Airplanes |
Author |
: Kenneth P. Spreemann |
Publisher |
: |
Release |
: 1957 |
File |
: 644 Pages |
ISBN-13 |
: STANFORD:36105024832128 |
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BOOK EXCERPT:
Product Details :
Genre |
: Airplanes |
Author |
: Kenneth P. Spreemann |
Publisher |
: |
Release |
: 1957 |
File |
: 56 Pages |
ISBN-13 |
: UOM:39015086414482 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: Kenneth P. Spreemann |
Publisher |
: |
Release |
: 1953 |
File |
: 46 Pages |
ISBN-13 |
: OCLC:1109679292 |
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BOOK EXCERPT:
Product Details :
Genre |
: Aerodynamics, Transonic |
Author |
: Thomas L. Fischetti |
Publisher |
: |
Release |
: 1954 |
File |
: 24 Pages |
ISBN-13 |
: UOM:39015086506964 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: Ellery B. Jr May |
Publisher |
: |
Release |
: 1951 |
File |
: 25 Pages |
ISBN-13 |
: OCLC:1109548256 |
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BOOK EXCERPT:
A limited investigation was made at high subsonic speeds to determine the effects of a wing leading-edge radius on the aerodynamic characteristics of a sweptback-wing-fuselage combination with leading-edge flaps and chord-extensions. The basic wing had 45 degree sweepback, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section. The leading-edge shapes considered consisted of a sharp leading edge, a normal airfoil leading edge, and a leading edge formed by using three times the normal radius and fairing the new nose contour smoothly into the normal airfoil. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.80 to 0.92 and an angle-of-attack range of -2 to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations with leading-edge flap deflections of 0 to 6 degrees.
Product Details :
Genre |
: Airplanes |
Author |
: Kenneth P. Spreemann |
Publisher |
: |
Release |
: 1955 |
File |
: 42 Pages |
ISBN-13 |
: OCLC:721356545 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: Kenneth P. Spreemann |
Publisher |
: |
Release |
: 1953 |
File |
: 36 Pages |
ISBN-13 |
: OCLC:1109715120 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: F.E. Jr West |
Publisher |
: |
Release |
: 1953 |
File |
: 40 Pages |
ISBN-13 |
: OCLC:1109598017 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: Kenneth W. Goodson |
Publisher |
: |
Release |
: 1953 |
File |
: Pages |
ISBN-13 |
: OCLC:1109668688 |
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BOOK EXCERPT:
Product Details :
Genre |
: |
Author |
: |
Publisher |
: |
Release |
: 1953 |
File |
: 43 Pages |
ISBN-13 |
: OCLC:713226570 |