Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Aerodynamic Load Measurements And Opening Characteristics Of Automatic Leading Edge Slats On A 45c Sweptback Wing At Transonic Speeds
Download Aerodynamic Load Measurements And Opening Characteristics Of Automatic Leading Edge Slats On A 45c Sweptback Wing At Transonic Speeds full books in PDF, epub, and Kindle. Read online Aerodynamic Load Measurements And Opening Characteristics Of Automatic Leading Edge Slats On A 45c Sweptback Wing At Transonic Speeds ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45 Degree Sweptback Wing at Transonic Speeds by : Donald D. Arabian
Download or read book Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45 Degree Sweptback Wing at Transonic Speeds written by Donald D. Arabian and published by . This book was released on 1961 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45° Sweptback Wing at Transonic Speeds by : Donald D. Arabian
Download or read book Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45° Sweptback Wing at Transonic Speeds written by Donald D. Arabian and published by . This book was released on 1961 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88 by : John A. Kelly
Download or read book Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88 written by John A. Kelly and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.
Book Synopsis Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by : Charles F. Whitcomb
Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Book Synopsis Aerodynamic Loads on a Leading-edge Flap and a Leading-edge Slat on the NACA 64A010 Airfoil Section by : John A. Kelly
Download or read book Aerodynamic Loads on a Leading-edge Flap and a Leading-edge Slat on the NACA 64A010 Airfoil Section written by John A. Kelly and published by . This book was released on 1954 with total page 706 pages. Available in PDF, EPUB and Kindle. Book excerpt: A previous report, NACA TN 3007, gave force and moment data for the NACA 64A010 airfoil section equipped alternately with a flap and a slat at the leading edge, and with a split flap and a double-slotted flap at the trailing edge. The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA 3007. The pressure data for the leading-edge flap and slat have been converted into coefficients of normal force, chord force, and moment based on the geometry of the leading-edge device.
Book Synopsis Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section by : William C. Sleeman
Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Book Synopsis Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections by : Jack F. Runckel
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections written by Jack F. Runckel and published by . This book was released on 1956 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Book Synopsis Aerodynamic Characteristics of a Small-scale Straight and Swept-back Wing with Knee-blown Jet Flaps by :
Download or read book Aerodynamic Characteristics of a Small-scale Straight and Swept-back Wing with Knee-blown Jet Flaps written by and published by . This book was released on 1977 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 by : Earl D. Knechtel
Download or read book Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 written by Earl D. Knechtel and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Book Synopsis Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge by : Warren A. Tucker
Download or read book Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge written by Warren A. Tucker and published by . This book was released on 1948 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.
Book Synopsis Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds by : John P. Mugler
Download or read book Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds written by John P. Mugler and published by . This book was released on 1956 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
Book Synopsis Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and Naca 65a004 Airfoil Sections by : JACK F. RUNCKEL
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and Naca 65a004 Airfoil Sections written by JACK F. RUNCKEL and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
Book Synopsis Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel by : Rodger L. Naeseth
Download or read book Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel written by Rodger L. Naeseth and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
Book Synopsis Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by : Marlowe D. Cassetti
Download or read book Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 written by Marlowe D. Cassetti and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
![Download Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 PDF Online Free](https://books.google.com/books/content/images/frontcover/LxEd41YqfAkC?fife=w200-h370)
