Download or read book Wind Tunnel Investigation of the Suitability of a Wing of N A C A 2412 Section for the Fairchild Super 71 Aircraft written by and published by . This book was released on 1934 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Tests on a 1 10th Scale Model of the Fairchild Super 71 Aircraft written by J. J. Green and published by . This book was released on 1934 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Control Surface Characteristics written by H. Page Hoggard and published by . This book was released on 1943 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force-test measurements in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel to determine the aerodynamic effects of changing the alignment of the cover plates on a sealed internally balanced flap. An NACA 0015 airfoil was utilized for the tests. The chord of the straight-contour flap was 30 percent of the airfoil chord and the balance with 50 percent of the flap chord.
Download or read book Wind Tunnel Tests on a Model of the Fairchild Super 71 Aircraft with Various Types of Forward Cockpit written by J. J. Green and published by . This book was released on 1935 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of an NACA 23021 Airfoil with a 0 32 airfoil chord Double Slotted Flap written by Jack Fischel and published by . This book was released on 1944 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was made in the LMAL 7- by 10-foot wind tunnel of an NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined.
Download or read book Wind tunnel Investigation at High Subsonic Speeds of the Effect of Spoiler Profile on the Lateral Control Characteristics of a Wing fuselage Combination Winter Quarter chord Line Swept Back 32 6 and NACA 65A006 Airfoil Section written by Harold S. Johnson and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated Balanced Double Split Flaps for Use as Aerodynamic Brakes written by Thomas A. Toll and published by . This book was released on 1945 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests have been made in the Langley 7- by 10-foot tunnel to determine the applicability of nonperforated, balanced double split flaps for use as aerodynamic brakes. Information was desired on the braking power of the flaps as well as on the effectiveness and the stability of a conventional trailing-edge aileron located immediately behind the flaps. A rectangular 10- by 60-inch wing model of NACA 2212 airfoil section was used for the tests. Results were obtained for flat-plate flaps with no wing cut-outs and for flaps having Clark Y sections with cut-outs made in the wing to simulate the space left open by the deflected flaps. The flap deflections, the chordwise location, and the gaps between the flaps and the airfoil contour were varied over wide ranges in order to determine the optimum configuration. In addition to the force tests, an investigation was made to determine any buffeting tendencies of the aileron. Silk tufts and a flexible torque rod were used for these tests.
Download or read book Wind tunnel Investigation of a Deflected slipstream Cruise fan V STOL Aircraft Wing written by William A. Newsom and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind tunnel Investigation of the Effects of Aspect Ratio Spanwise Variations in Section Thickness Ratio and a Body Indentation on the Aerodynamic Characteristics of a 45 Sweptback Wing body Combination written by Melvin M. Carmel and published by . This book was released on 1953 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Summary of Results of a Wind tunnel Investigation of Nine Related Horizontal Tails written by Jules B. Dods and published by . This book was released on 1955 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7 degrees to 45 degrees, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models.
Download or read book Wind tunnel Investigation of Control surface Characteristics written by H. Page Hoggard and published by . This book was released on 1944 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The 15-percent bevel was tested with the bevel corner faired with both large and small radii. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of the horizontal and vertical tail surfaces.
Download or read book Wind tunnel Investigation at Low Speed of the Effect of Varying the Ratio of Body Diameter to Wing Span from 0 1 to 0 8 on the Aerodynamic Characteristics in Pitch of the 45 Sweptback wing body Combination written by Harold S. Johnson and published by . This book was released on 1953 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of Control surface Characteristics written by John M. Riebe and published by . This book was released on 1945 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made to investigate the characteristics of an NACA 0009 airfoil with a 40-percent-chord flap having medium and large aerodynamic balances of elliptical and blunt nose shapes and having a plain overhang. The results are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed and unsealed. Tests were also made to determine the effectiveness of a tab, which was 20 percent of the flap chord, on the plain sealed flap and on the 35-percent-flap-chord elliptical-overhang flap with gap sealed. The pressure difference across the flap-nose seal was also determined for the plain sealed flap.
Download or read book Results of Full scale Wind Tunnel Tests on the H 126 Jet Flap Aircraft written by Anthony M. Cook and published by . This book was released on 1969 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of NACA 66 215 216 66 1 212 and 651 212 Airfoils with 0 20 airfoil chord Split Flaps written by Felicien F. Fullmer and published by . This book was released on 1944 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was carried out in the NACA two-dimensional low-turbulence pressure tunnel of the NACA 66(215)-216, 66,1-212, and 651-212 airfoil sections equipped with split flaps having chords 20 percent of the airfoil chord. The purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps. All the present tests were made at a Reynolds number of approximately 6 x 106 and a Mach number of about 0.15.
Download or read book Wind Tunnel Investigation of Effect of Yaw on Lateral stability Characteristics written by Isidore G. Recant and published by . This book was released on 1942 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Download or read book Wind tunnel Investigation of Control surface Characteristics written by M. Leroy Spearman and published by . This book was released on 1945 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap having a chord 25 percent of the airfoil chord and a balancing tab having a chord 50 percent of the airfoil chord or 200 percent of the flap chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested on the model. The tests indicated that the flap and tab could be linked to give hinge-moment balance with flap deflection and with angle of attack and yet have greater lift effectiveness than a plain flap of similar size with a conventional balancing tab having a chord 20 percent of the flap chord linked to give hinge-moment balance with flap deflection only.
