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Wind Tunnel Investigation Of The Lift Characteristics Of An Naca 27 212 Airfoil With Two Types Of Flap
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Book Synopsis Wind-tunnel Investigation of the Lift Characteristics of an NACA 27-212 Airfoil with Two Types of Flap by : Robert S. Swanson
Download or read book Wind-tunnel Investigation of the Lift Characteristics of an NACA 27-212 Airfoil with Two Types of Flap written by Robert S. Swanson and published by . This book was released on 1940 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 airfoil with a 20-percent-chord split flap and with two arrangements of a 25.66-percent-chord slotted flap to determine the section lift characteristics as affected by flap deflection, flap position, and slot shape for the slotted flap. For the two arrangements of the slotted flap, the flap positions for maximum section lift are given. Comparable data on the NACA 23012 airfoil equipped with similar flaps are also given.
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
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 616 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of NACA 66(215)-216, 66,1-212, and 651-212 Airfoils with 0.20-airfoil-chord Split Flaps by : Felicien F. Fullmer
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.
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
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 664 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : John M. Riebe
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.
Book Synopsis Wind-tunnel Investigation of an NACA 23021 Airfoil with a 0.32-airfoil-chord Double Slotted Flap by : Jack Fischel
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.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : Robert B. Liddell
Download or read book Wind-tunnel Investigation of Control-surface Characteristics written by Robert B. Liddell and published by . This book was released on 1944 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made in two-dimensional flow to investigate the aerodynamic characteristics of a double flap with an internal and an overhang balance. Three sizes of each type of balance were tested with three relative rates of deflection of the two flaps. An NACA 66-009 airfoil having a 0.30-airfoil-chord straight-contour forward flap and a 0.20-airfoil-chord straight-contour rearward flap was used. The test results indicated that a balanced double flap produced the same lift as a single plain flap of the same chord and also produced highly balanced hinge moments. High lifts and low hinge moments were obtained with a double-flap arrangement if either an overhang or an internal balance having a chord 50 percent of the flap chord was incorporated on the forward flap. The overhang-balance flap showed a lower value of the hinge-moment gradient due to flap deflection than the internally balanced flap.
Book Synopsis Two-dimensional Wind-tunnel Investigation of Four Types of High-lift Flap on an NACA 65-210 Airfoil Section by : Jones F. Cahill
Download or read book Two-dimensional Wind-tunnel Investigation of Four Types of High-lift Flap on an NACA 65-210 Airfoil Section written by Jones F. Cahill and published by . This book was released on 1947 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : John M. Riebe
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 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord. The pressure difference across the flap seal was also determined for the plain sealed flap.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : M. Leroy Spearman
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.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : H. Page Hoggard
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.
Book Synopsis The Wind and Beyond: The ascent of the airplane by : James R. Hansen
Download or read book The Wind and Beyond: The ascent of the airplane written by James R. Hansen and published by . This book was released on 2003 with total page 990 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Report by : United States. National Advisory Committee for Aeronautics
Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Investigation of Control Surface Characteristics by : H. Page Hoggard
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.
Book Synopsis Two-dimensional Wind-tunnel Investigation of the NACA 641-012 Airfoil Equipped with Two Types of Leading-edge Flap by : Felicien F. Fullmer
Download or read book Two-dimensional Wind-tunnel Investigation of the NACA 641-012 Airfoil Equipped with Two Types of Leading-edge Flap written by Felicien F. Fullmer and published by . This book was released on 1947 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Langley two-dimensional low-turbulence pressure tunnel to determine the characteristics of leading edge flaps used as high-lift devices. the investigation, conducted at a Reynolds number of 6.0 x 106, included to slide forward along the upper surface and the other hinged near the leading edge on the lower surface of an NACA 641-012 airfoil, with and without a 20-percent chord trailing-edge split flap. Data are given to show the section lift characteristics for a range of flap deflections and the pitching-moment characteristics and lift characteristics with leading-edge roughness for the optimum flap arrangements.
Book Synopsis Wind-tunnel Investigation of NACA 66(215)-216, 66,1-212, and 65(1)-212 Airfoils with 0.20-airfoil-chord Split Flaps by : Felicien F. Fullmer
Download or read book Wind-tunnel Investigation of NACA 66(215)-216, 66,1-212, and 65(1)-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 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was carried out in the NACA two-dimensional low-turbulence pressure tunnel of the NACA 66(215)-216, 66,1-212, and 65(sub-1)-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 present tests were made at a Reynolds number of approximately 6,000,000 and a Mach number of about 0.15.
Book Synopsis Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap by : Jerry V. Kirk
Download or read book Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap written by Jerry V. Kirk and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
