Download or read book Wind tunnel Investigation of an NACA 23012 Airfoil with a 30 Percent Chord Maxwell Slate and with Trailing edge Flaps written by John G. Lowry and published by . This book was released on 1941 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil with a 30-percent-chord Maxwell leading-edge slat and with a slotted and a split flap. The purpose of the investigation was to determine the optimum slot gap of the Maxwell slat for, and the aerodynamic section characteristics of, the airfoil with several deflections of both types of flap. Curves of lift, drag, and pitching-moment characteristics for selected optimum arrangements are presented.
Download or read book Wind tunnel Investigation of an NACA 23012 Airfoil with an 18 05 Percent Chord Maxwell Slat and with Trailing edge Flaps written by Clarence L. Gillis and published by . This book was released on 1941 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made to determine the optimum slot gap of he Maxwell slat for and the aerodynamic section characteristics, of the NACA 23012 airfoil with several deflections of a slotted and a split flap. It was found that, for he combinations tested, a slot gap of 0.0175 c was the optimum. This gap appreciably increased the maximum lift coefficient and angle of attack at the stall. The effectiveness of the slat, however, dropped with increasing flap deflection.
Download or read book Wind Tunnel Investigation of an NACA 23012 Airfoil with 30 Percent Chord Venetian Blind Flaps written by F.M. Rogallo and published by . This book was released on 1942 with total page 8 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 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 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 of an NACA 23012 Airfoil with a 0 30 airfoil chord Double Slotted Flap written by Paul E. Purser and published by . This book was released on 1942 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests to determine the effect of flap position and deflection on the aerodynamic characteristics of an NACA 23012 airfoil with a double slotted flap having a chord 30 percent of the airfoil chord (0.30c) were conducted in the LMAL 7- by 10-foot tunnel. In addition, a few tests were made to determine the aerodynamic section characteristics as affected by the size and shape of the fore flap, by movement of the fore flap and rear flap as a unit, and by variation in the airfoil lower lip. Contours of rear-flap-nose position for various values of maximum section lift coefficient, section profile-drag coefficient, and section pitching-moment coefficient are presented at three selected fore-flap positions for various rear-flap deflections. The complete aerodynamic section characteristics are given at the three selected fore-flap positions for the optimum-lift and optimum-drag positions of the rear flap at several deflections.
Download or read book Wind tunnel Investigation of an NACA 23012 Airfoil with Several Arrangements of Slotted Flaps with Extended Lips written by John G. Lowry and published by . This book was released on 1941 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip location on the aerodynamic section characteristics of an NACA 23012 airfoil with a 30-percent-chord slotted flap. Tests were made with slot lips located at 90 and 100 percent of the airfoil chord and with two different flap shapes.
Download or read book Wind tunnel Investigation of an N A C A 23012 Airfoil with Two Arrangements of a 40 percent chord Slotted Flap written by Frank Duschik and published by . This book was released on 1940 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of an N A C A 23012 Airfoil with a 0 30 airfoil chord Double Slotted Flap written by Paul E. Purser and published by . This book was released on 1944 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of an NACA 23012 Airfoil with Two Arrangements of a Wide chord Slotted Flap written by Thomas A. Harris and published by . This book was released on 1939 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of NACA 23012 23021 and 23030 Airfoils Equipped with 40 Percent Chord Double Slotted Flaps written by Thomas A. Harris and published by . This book was released on 1941 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of an NACA 23012 Airfoil with Two Sizes of Balanced Split Flap written by Thomas A. Harris and published by . This book was released on 1940 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil with a 15-percent-chord and a 25-percent-chord balanced split flap of the Clark Y profile. The investigation was made to determine the aerodynamic section characteristics of the airfoil as affected by the size, nose location, and deflection of the flap. Complete aerodynamic section characteristics were determined for several nose locations of each flap and are presented for four typical locations for each flap. A comparison of the drag and lift characteristics is made with two other medium-chord flaps previously investigated.
Download or read book Wind tunnel Investigation of an N A C A 23012 Airfoil with Two Arrangements of a Wide chord Slotted Flap written by Thomas Anthony Harris and published by . This book was released on 1939 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the N.A.C.A. 7- by 10-foot wind tunnel of a large-chord N.A.C.A. 23012 airfoil with several arrangements of a 40-percent-chord slotted flap to determine the section aerodynamic characteristics of the airfoil as affected by slot shape, flap location, and flap deflection. The flap positions for maximum lift, the polars for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determined. A discussion is given of the relative merits of the various arrangements. A comparison is made of slotted flaps of different chords on the N.A.C.A. 23012 airfoil.
Download or read book NACA Research Memorandum written by and published by . This book was released on 19?? with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of an NACA Full span High lift Lateral control Combination written by Francis Melvin Rogallo and published by . This book was released on 1942 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of several arrangements of an NACA full-span high-lift lateral-control combination. The combination is essentially a full-span flap of airfoil profile that retracts ahead of a narrow-chord full-span aileron. In the flap-retracted condition the aileron is a conventional trailing-edge aileron of short chord and long span. In the flap-deflected condition the flap is similar to a Fowler flap and the aileron becomes a full-span slot-lip aileron. The aileron is drooped in the flap-deflected condition to improve high-lift characteristics. Tests were run at several aileron and flap angles and with several widths of slot to determine the optimum arrangement.
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.
