Download or read book The Use of a Leading edge Area suction Flap and Leading edge Modifications to Improve the High lift Characteristics of an Airplane Model with a Wing of 45 Degree Sweep and Aspect Ratio 2 8 written by David G. Koenig and published by . This book was released on 1957 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was undertaken on an airplane model with drooped horizontal tail and a highly tapered wing of aspect ratio sweep. The investigation was designed to determine what improvements in the control of leading-edge stall would be possible with the use of area suction on a le--edge flap and with the leading-edge flap used with a modified or bulbous leading edge and a chord extension. Two spans of area-suction trailing-edge flap were tested. The tests were made at a Reynolds number of 8,900,000.
Download or read book The Use of a Leading edge Area suction Flap and Leading edge Modifications to Improve the High lift Characteristics of an Airplane Model with a Wing of 45 Sweep and Aspect Ratio of 2 8 written by David G. Koenig and published by . This book was released on 1958 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Use of Area Suction to Increase the Effectiveness of Trailing edge Flaps of Various Spans on a Wing of 45 Degree Sweepback and Aspect Ratio 6 written by Roy N. Griffin and published by . This book was released on 1956 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made of a model with a wing of 45 degree sweepback and aspect ratio of 6 to determine the aerodynamic characteristics and suction requirements for boundary-layer control by means of area suction applied to trailing-edge flaps. Included in this study were limited tests to use the differentially deflected flaps for lateral control. Flap spans extending from 0.12 b/2 to 0.50, 0.66, and 0.83 b/2 were tested at various flap deflections at 46 degrees and 65 degrees on the 0.12 to 0.50 b/2 spans with boundary-layer control applied. A limited number of the tests were made with area suction applied to the wing leading edge.
Download or read book Analysis of Factors Affecting Net Lift Increment Attainable with Trailing edge Split Flaps on Tailless Airplanes written by Marvin Pitkin and published by . This book was released on 1945 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis has been made of factors affecting the net lift increment attainable with trailing-edge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitching-moment characteristics of flaps of this type over a range of design conditions in which sweepback angle, aspect ratio, taper ratio, flap chord, and flap deflection were widely varied. In addition, calculations were made to determine the effect of the various parameters upon the loss in lift incurred in trimming the stability moments of a tailless airplane. A method is given for roughly estimating the maximum lift coefficient of tailless airplanes.
Download or read book The Use of Area Suction for Improving the Longitudinal Characteristics of a Thin Unswept Wing fuselage Model with Leading and Trailing edge Flaps written by David G. Koenig and published by . This book was released on 1956 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effect of porous area suction applied to the knees of full-span leading-edge and part-span trailing-edge flaps installed on an unswept-wing airplane model. The wind was of aspect ratio 3 and had a modified double-wedge section with a thickness of 4.2-percent chord. For a brief test, an unswept horizontal tail was installed on the model 0.62 semispan above the exended wing-chord plane. Most of the tests were made at a Reynolds number of 9,400,000 and a Mach number of 0.11.
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 Effect of a Leading Edge Flap Upon the Lift Drag and Pitching Moment of an Airplane Employing a Thin Unswept Wing written by John C. Heitmeyer and published by BiblioGov. This book was released on 2013-07 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of deflecting full-span, constant-chord, leading-edge flaps, having either round or sharp leading edges, upon the lift, drag, . and pitching moment characteristics of a model of an interceptor-type aircraft have been determined experimentally at subsonic and supersonic speeds. Results indicate that the variations of lift with angle of attack and of pitching moment with lift were unaffected by either the shape of the flap leading edge or flap deflection. Deflection of the flaps having either a round or sharp leading edge increased the drag at zero lift at both subsonic and supersonic speeds. In spite of the increase in the drag at zero lift, however, deflection of the flaps increased the maximum lift-drag ratio at subsonic speeds and had no deleterious effect at supersonic speeds
Download or read book The Use of Area Suction to Increase the Effectiveness of a Trailing edge Flap on a Triangular Wing of Aspect Ratio 2 written by Mark W. Kelly and published by . This book was released on 1954 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Application of Area Suction to Leading edge and Trailing edge Flaps on a 44 Degree Swept wing Model written by Curt A. Holzhauser and published by . This book was released on 1956 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was conducted with a 44 degree swept-wing model to determine the effects leading- and trailing-edge area-suction flaps have on the static longitudinal characteristics of this model, and to measure the suction requirements of the flaps.
Download or read book The Effects of an Inverse taper Leading edge Flap on the Aerodynamic Characteristics in Pitch of a Wing body Combination Having an Aspect Ratio of 3 and 45 Degrees of Sweepback at Mach Numbers to 0 92 written by Fred A. Demele and published by . This book was released on 1958 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of 3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16 degrees.
Download or read book The Effects of an Inverse taper Leading edge Flap on the Aerodynamic Characteristics in Pitch of a Wing body Combination Having an Aspect Ratio of 3 and 45 degrees of Sweptback at Mach Numbers to 0 92 written by Fred A. Demele and published by . This book was released on 1958 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Leading edge Suction on Lift drag Ratios of Wings at Supersonic Speeds written by Clarence B. Cohen and published by . This book was released on 1948 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: The possible gain in lift-drag ratio for region of wing affected by tip increases as the sweepback of wing is increased. An appropriately curved tip gives higher lift-drag ratios than the best trapezoidal tip.
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 The Effects of Trailing edge Flaps on the Subsonic Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 written by Bruce E. Tinling and published by . This book was released on 1955 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Use of Leading edge Area Suction to Increase the Maximum Lift Coefficient of a 35 Degrees Swept back Wing written by Curt A. Holzhauser and published by . This book was released on 1953 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Leading edge High lift Devices and Split Flaps on the Maximum lift and Lateral Characteristics of a Rectangular Wing of Aspect Ratio 3 4 with Circular arc Airfoil Sections at Reynolds Numbers from 2 9 X 10 6 to 8 4 X 10 6 written by Roy H. Lange and published by . This book was released on 1948 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Use of Leading edge Area Suction to Increase the Maximum Lift Coefficient of a 35 Degree Swept back Wing written by Curt A. Holzhauser and published by . This book was released on 1952 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
