Download or read book Low speed Investigation of Leading edge and Trailing edge Flaps on a 47 5 Degree Sweptback Wing of Aspect Ratio 3 4 at a Reynolds Number of 4 4 X 10 6 written by Jerome Pasamanick and published by . This book was released on 1950 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 734 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Leading edge Devices and Trailing edge Flaps on Longitudinal Characteristics of Two 47 7 Degrees Sweptback Wings of Aspect Ratios 5 1 and 6 0 at a Reynolds Number of 6 0 X 10 6 written by Reino J. Salmi and published by . This book was released on 1950 with total page 105 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Investigation of Several Types of Split Flap on a 47 7 Degree Sweptback wing fuselage Combination of Aspect Ratio 5 1 at a Reynolds Number of 6 0 X 10 6 written by Stanley H. Spooner and published by . This book was released on 1951 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. 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.

Download or read book Low speed Longitudinal Characteristics of a Circular arc 52 Degrees Sweptback Wing of Aspect Ratio 2 84 with and Without Leading edge and Trailing edge Flaps at Reynolds Number from 1 6 X 10 6 to 9 7 X 10 6 written by Gerald V. Foster and published by . This book was released on 1950 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerospace Engineering Index written by and published by . This book was released on 1951 with total page 612 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Longitudinal and Wake Air flow Characteristics at a Reynolds Number of 6 0 X 10 6 of a 52 Degree Sweptback Wing Equipped with Various Spans of Leading edge and Trailing edge Flaps a Fuselage and a Horizontal Tail at Various Vertical Positions written by Roland F. Griner and published by . This book was released on 1951 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Investigation of the Aerodynamic Loads on the Droop nose Flap of a Wing with Leading Edge Swept Back 47 5 Degrees and Having Symmetrical Circular arc Airfoil Sections at a Reynolds Number of 4 3 X 10 6 written by Edward F. Jr Whittle and published by . This book was released on 1950 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Wind tunnel Investigation of Blowing Boundary layer Control on Leading and Trailing edge Flaps of a Full scale Low aspect ratio 42 Swept wing Airplane Configuration written by Ralph L. Maki and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Investigation of the Effects of Single Slotted and Double Slotted Flaps on a 47 7 Degrees Sweptback wing Fuselage Combination at a Reynolds Number of 6 0 X 10 6 written by Mollenberg (Ernst F.) and published by . This book was released on 1951 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers of 0 40 to 0 93 of a 45 Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering Index written by and published by . This book was released on 1952 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of Semispan and Full span Tests of A 47 5 Degrees Sweptback Wing with Symmetrical Circular arc Sections and Having Drooped nose Flaps Trailing edge Flaps and Ailerons written by Stanley Lipson and published by . This book was released on 1951 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley full-scale tunnel to determine the comparative characteristics of a full-span and semispan 47.5 degrees sweptback wing having 10-percent thick biconvex airfoil sections and an aspect ratio of 3.5. The configurations tested were the basic wing, the wing with various combinations of leading- and trailing edge flaps, and the basic wing with an aileron deflection. The results included both force and pressure measurements and were obtained at a Reynolds number of 4,200,000 and a Mach number of 0.07.

Download or read book Effect of Leading And Trailing Edge Flaps on Clipped Delta Wings with and Without Wing Camber at Supersonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the aerodynamic characteristics of thin, moderately swept fighter wings has been conducted to evaluate the effect of camber and twist on the effectiveness of leading- and trailing-edge flaps at supersonic speeds in the Langley Unitary Plan Wind Tunnel. The study geometry consisted of a generic fuselage with camber typical of advanced fighter designs without inlets, canopy, or vertical tail. The model was tested with two wing configurations an uncambered (flat) wing and a cambered and twisted wing. Each wing had an identical clipped delta planform with an inboard leading edge swept back 65 deg and an outboard leading edge swept back 50 deg. The trailing edge was swept forward 25 deg. The leading-edge flaps were deflected 4 deg to 15 deg, and the trailing-edge flaps were deflected from -30 deg to 10 deg. Longitudinal force and moment data were obtained at Mach numbers of 1.60, 1.80, 2.00, and 2.16 for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.16 x 10(exp 6) per foot and for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.0 x 10(exp 6) per foot. Vapor screen, tuft, and oil flow visualization data are also included. Hernandez, Gloria and Wood, Richard M. and Covell, Peter F. Langley Research Center RESEARCH; INVESTIGATION; DESIGN; EXPLORATION...

Download or read book Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing body tail Configuration in Combination with Leading edge Devices written by H. Clyde McLemore and published by . This book was released on 1956 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel to determine the effects on the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. The wing and horizontal tail have an aspect ratio of 3.5, taper ratio of 0.3, leading-edge sweep of 49 degrees, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The trailing-edge air was ejected over highly deflected half- and full-span flaps in combination with several leading-edge-flow control devices including blowing from a slot in the wing leading edge. The momentum coefficient range was investigated was 0 to 0.16 for the trailing-edge blowing and 0 to 0.025 for the leading-edge blowing. Most of the tests were conducted at a Reynolds number of 5,200,000 corresponding to a Mach number of 0.08.