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Investigation Of Naca 642 432 And 643 440 Airfoil Sections With Boundary Layer Control And An Analytical Study Of Their Possible Applications
Download Investigation Of Naca 642 432 And 643 440 Airfoil Sections With Boundary Layer Control And An Analytical Study Of Their Possible Applications full books in PDF, epub, and Kindle. Read online Investigation Of Naca 642 432 And 643 440 Airfoil Sections With Boundary Layer Control And An Analytical Study Of Their Possible Applications ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Investigation of NACA 64,2-432 and 64,3-440 Airfoil Sections with Boundary-layer Control and an Analytical Study of Their Possible Applications by : Elmer A. Horton
Download or read book Investigation of NACA 64,2-432 and 64,3-440 Airfoil Sections with Boundary-layer Control and an Analytical Study of Their Possible Applications written by Elmer A. Horton and published by . This book was released on 1951 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made to determine the effect of boundary-layer control by means of suction through a slot of 0.60c on the pressure distribution, lift, and drag characteristics of the NACA 64,2-432 and 64,3-440 airfoil sections. The effect on the section aerodynamic characteristics of boundary-layer control by means of a slot at 0.50c and by means of area suction from 0.55c to 0.71c was also investigated for the NACA 64,3-440 airfoil. An analysis was made to show the effect of such thick airfoil sections and boundary-layer control on the lift-drag ratio of a wing. The section data presented and employed in the analysis to the leading edges of the models. This roughness was probably more severe than that likely to be encountered on practical aircraft under normal operating conditions; therefore, the drag coefficients measured bot with and without boundary layer control may be somewhat high as compared with practical flight values.
Book Synopsis Research Investigation of Boundary Layer Control by Blowing on the N.A.C.A. 23012 and 23015 Airfoil Sections with Various Flaps by : Jack W. Fisher
Download or read book Research Investigation of Boundary Layer Control by Blowing on the N.A.C.A. 23012 and 23015 Airfoil Sections with Various Flaps written by Jack W. Fisher and published by . This book was released on 1950 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of the Boundary Layer on an NACA 0009 Airfoil Having 0.25- and 0.50-airfoil Chord Plain Sealed Flaps by : Jack D. Brewer
Download or read book Wind-tunnel Investigation of the Boundary Layer on an NACA 0009 Airfoil Having 0.25- and 0.50-airfoil Chord Plain Sealed Flaps written by Jack D. Brewer and published by . This book was released on 1948 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 4- by 6-foot tunnel to determine the boundary-layer characteristics of an NACA 0009 airfoil equipped with 0.25- and 0.50-airfoil chord plain sealed flaps. The tests were made to define as thoroughly as possible the characteristics of two of the configurations used in a comprehensive investigation of control surface characteristics and also to provide additional data for comparison with previous boundary-layer analyses. The measured velocity profiles and the boundary-layer parameters determined from them are presented.
Book Synopsis Experimental Investigation of an NACA 64A010 Airfoil Section with 41 Suction Slots on Each Surface for Control of Laminar Boundary Layer by : Dale L. Burrows
Download or read book Experimental Investigation of an NACA 64A010 Airfoil Section with 41 Suction Slots on Each Surface for Control of Laminar Boundary Layer written by Dale L. Burrows and published by . This book was released on 1952 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation of an NACA 64A010 airfoil model with 41 suction slots per surface indicated that laminar flow could be obtained over 0.91 chord on one surface up to a Reynolds number of 10,000,000 with an estimated net drag saving of about 50 percent over the plain smooth airfoil. Extensive laminar flow could not be obtained at higher Reynolds numbers because of increased sensitivity of the flow to minute surface irregularities and slight inaccuracies of slot-entry contour.
Book Synopsis Wind-tunnel Investigation of Boundary-layer Control by Blowing on an NACA 655-424 Airfoil to Effect Drag Reduction by : Thomas R. Turner
Download or read book Wind-tunnel Investigation of Boundary-layer Control by Blowing on an NACA 655-424 Airfoil to Effect Drag Reduction written by Thomas R. Turner and published by . This book was released on 1964 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Boundary-layer Control to Improve the Lift and Drag Characteristics of the NACA 65 2-415 Airfoil Section with Double Slotted and Plain Flaps by : Elmer A. Horton
Download or read book Investigation of Boundary-layer Control to Improve the Lift and Drag Characteristics of the NACA 65 2-415 Airfoil Section with Double Slotted and Plain Flaps written by Elmer A. Horton and published by . This book was released on 1950 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Laminar Flow Aircraft Certification by :
Download or read book Laminar Flow Aircraft Certification written by and published by . This book was released on 1986 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Boundary Layers Near the Stagnation Point of an Oscillating Airfoil by : Tuncer Cebeci
Download or read book Calculation of Boundary Layers Near the Stagnation Point of an Oscillating Airfoil written by Tuncer Cebeci and published by . This book was released on 1983 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of an investigation of boundary layers close to the stagnation point of an oscillating airfoil are reported. Two procedures for generating initial conditions - the characteristics-box scheme and a quasi-static approach - were investigated, and the quasi-static approach was shown to be appropriate provided the initial region was far from any flow separation. With initial conditions generated in this way, the unsteady boundary-layer equations were solved for the flow in the leading-edge region of a NACA 0012 airfoil oscillating from 0 degrees to 5 degrees. Results were obtained for both laminar and turbulent flow, and, in the latter case, the effect of transition was assessed by specifying its occurrence at different locations. The results demonstrate the validity of the numerical scheme and suggest that the procedures should be applied to calculation of the entire flow around oscillating airfoils. (Author).
Book Synopsis The Boundary-layer and Stalling Characteristics of the NACA 64A010 Airfoil Section by : Robert F. Peterson
Download or read book The Boundary-layer and Stalling Characteristics of the NACA 64A010 Airfoil Section written by Robert F. Peterson and published by . This book was released on 1950 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was conducted to determine boundary-layer and stalling characteristics of the NACA 64A010 airfoil section. Data obtained include force measurements, liquid-film studies, and pressure-distribution and boundary-layer measurements. The region of separated flow which appeared on the upper surface near the leading edge is discussed.
Book Synopsis Tests of the NACA 641A212 Airfoil Section with a Slat, a Double Slotted Flap, and Boundary-layer Control by Suction by : John H. Quinn
Download or read book Tests of the NACA 641A212 Airfoil Section with a Slat, a Double Slotted Flap, and Boundary-layer Control by Suction written by John H. Quinn and published by . This book was released on 1947 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted of the NACA 641A212 airfoil section equipped with a leading edge slat, a double slotted flap, and a boundary-layer-control suction slot at 0.40 chord to determine the maximum lift coefficients attainable with these high-lift devices alone and in conjuction with one another. Tests were made over a range of Reynolds number from 1,000,000 to 6,000,000 and included surveys to find the optimum configurations for the slat and flap.
Book Synopsis Investigation of Boundary-layer Control to Improve the Lift and Drag Characteristics of the NACA 652-415 Airfoil Section with Double Slotted and Plain Flaps by : Elmer A. Horton
Download or read book Investigation of Boundary-layer Control to Improve the Lift and Drag Characteristics of the NACA 652-415 Airfoil Section with Double Slotted and Plain Flaps written by Elmer A. Horton and published by . This book was released on 1950 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation considered the effectiveness of two ways of using boundary-layer control to improve lift and drag of the NACA 652-415 airfoil section and the effect of section lift-drag ratio on that of an airplane having a wing composed of these sections. The models were tested in the smooth and rough conditions at Reynolds numbers of 1,000,000, 2,200,000, and 6,000,000 with an 0.30-chord double slotted flap and a suction slot at 0.76 chord. Maximum lift data are presented for an extensive range of airfoil thickness ratios.
Book Synopsis A Wind-tunnel Investigation of Boundary-layer Control by Suction on the NACA 653-418 by : John H. Quinn
Download or read book A Wind-tunnel Investigation of Boundary-layer Control by Suction on the NACA 653-418 written by John H. Quinn and published by . This book was released on 1946 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests have been been made to find the maximum lift of the NACA 653-418, a = 1.0 airfoil section equipped with a layer suction slot located at 0.45 airfoil chord. The tests were made at Reynolds numbers of 1.9, 3.4, and 6.0 x 106 for flap deflections ranging from 0 to 65 degrees and for flow coefficients ranging from 0 to 0.040. The flow coefficient is defined as the ratio of the quantity rate of air flow through the suction slot to the product of the wing area and free-stream velocity.
Book Synopsis Tests of the NACA 64-1-A212 Airfoil Section with a Slat, a Double Slotted Flap, and Boundary-layer Control by Suction by : John H. Quinn
Download or read book Tests of the NACA 64-1-A212 Airfoil Section with a Slat, a Double Slotted Flap, and Boundary-layer Control by Suction written by John H. Quinn and published by . This book was released on 1947 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720666233 Total Pages :40 pages Book Rating :4.6/5 (662 download)
Book Synopsis Probing Within the Boundary Layer of an Airfoil by Using the Wind Numerical Code by : National Aeronautics and Space Administration (NASA)
Download or read book Probing Within the Boundary Layer of an Airfoil by Using the Wind Numerical Code written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-04 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A detailed boundary layer investigation of an NACA 0012 airfoil was made by applying the WIND code at the NASA Glenn Research Center. Structured C-grids of selected configurations were fitted around the airfoil. Grids with dense spacing to capture the boundary layer provided for obtaining accurate results in this region. Concurrent with the boundary layer investigation, contour plots of overall performance of the airfoil were also obtained. A Mach number of 0.80, a Reynolds number of 4,000,000, and a zero angle of attack were set to correspond with numerical and experimental investigations reported in the literature, for comparison with the overall performance. The results were favorable for both the boundary layer investigations and the performance. As WIND evolves, it is intended to run WIND using unstructured grids to compare such results with the current structured grid results.Cavicchi, Richard H.Glenn Research CenterAIRFOILS; BOUNDARY LAYERS; STRUCTURED GRIDS (MATHEMATICS); MACH NUMBER; REYNOLDS NUMBER; ZERO ANGLE OF ATTACK; CONTOURS
Book Synopsis Wind-tunnel Investigation of the NACA 654-421 Airfoil Section with a Double Slotted Flap and Boundary-layer Control by Suction by : John H. Quinn
Download or read book Wind-tunnel Investigation of the NACA 654-421 Airfoil Section with a Double Slotted Flap and Boundary-layer Control by Suction written by John H. Quinn and published by . This book was released on 1947 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langely two-dimensional low-turbulence tunnel to find the effect of boundary-layer control on the aerodynamic characteristics of the NACA 654-421 airfoil section with a boundary-layer-control suction slot at 0.45 airfoil chord and a 0.32-airfoil-chord double slotted flap. This airfoil is designed primarily to obtain a high maximum lift coefficient. The tests consisted of lift measurements with the flap deflected and lift and drag measurements with the flap retracted over a range of flow coefficient from 0 to 0.3 for the model smooth and rough at Reynolds numbers of 1,000,000 and 2,200,000. The flow coefficient is defined as the ratio of the quantity rate of air flow removed through the suction slot to the product of the wing area and the free-stream velocity.
Book Synopsis A Study of Aerodynamic Control in Stalled Flight Long Laminar Separation Bubble Analysis by : Frank A. Dvorak
Download or read book A Study of Aerodynamic Control in Stalled Flight Long Laminar Separation Bubble Analysis written by Frank A. Dvorak and published by . This book was released on 1985 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes an analysis method for laminar separation bubbles (long or short) on two-dimensional airfoil sections at incidence. A viscous/potential flow iterative procedure was chosen due to its simple and efficient nature. The boundary layer procedure is a finite-difference method, sometimes referred to as the 'Bosx Scheme', and uses the Cebeci-Smith two-layer, eddy viscosity model for turbulence closure. The potential flow calculation in such a way that it gives constant pressure along the surface inside the bubble, The coupled calculation procedure has been applied to the NACA 64A006 airfoil and satisfactory results have been obtained.
Book Synopsis Boundary-layer and Stalling Characteristics of the NACA 64A006 Airfoil Section by : George B. McCullough
Download or read book Boundary-layer and Stalling Characteristics of the NACA 64A006 Airfoil Section written by George B. McCullough and published by . This book was released on 1949 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was conducted to determine the boundary-layer and stalling characteristics of an NACA 64A006 airfoil section. Force and pressure-distribution measurements, tuft studies, and boundary layer measurements were obtained for a Reynolds number of 5,800, 000.
