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Effects Of Compressibility On Lift And Load Characteristics Of A Tapered Wing Of Naca 64 210 Airfoil Sections Up To A Mach Number Of 060
Download Effects Of Compressibility On Lift And Load Characteristics Of A Tapered Wing Of Naca 64 210 Airfoil Sections Up To A Mach Number Of 060 full books in PDF, epub, and Kindle. Read online Effects Of Compressibility On Lift And Load Characteristics Of A Tapered Wing Of Naca 64 210 Airfoil Sections Up To A Mach Number Of 060 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Compressibility on Lift and Load Characteristics of a Tapered Wing of NACA 64-210 Airfoil Sections Up to a Mach Number of 0.60 by : F. E. West
Download or read book Effects of Compressibility on Lift and Load Characteristics of a Tapered Wing of NACA 64-210 Airfoil Sections Up to a Mach Number of 0.60 written by F. E. West and published by . This book was released on 1949 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of compressibility on the lift, pressure, pitching-moment, and load characteristics of a 12-foot tapered wing having NACA 64-210 airfoil sections and aspect ratio of 6 is presented for Mach numbers up to 0.60 and an angle-of-attack range of -4 degrees up through the stall.
Book Synopsis Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections by : E. O. Pearson
Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Book Synopsis Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections by : G. Chester Furlong
Download or read book Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections written by G. Chester Furlong and published by . This book was released on 1950 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1993 with total page 1356 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-chord Flap by : W. F. Lindsey
Download or read book Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-chord Flap written by W. F. Lindsey and published by . This book was released on 1946 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at 0.20 flap deflections from 0 to -12 degree. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
Book Synopsis Variation of Peak Pitching-moment Coefficients for Six Airfoils as Affected by Compressibility by : Harold E. Cleary
Download or read book Variation of Peak Pitching-moment Coefficients for Six Airfoils as Affected by Compressibility written by Harold E. Cleary and published by . This book was released on 1944 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution tests of six NACA 16-series propeller sections with 1-foot chords were conducted in the NACA 8-foot high-speed tunnel to determine the compressibility effects on peak section pitching-moment coefficients. The data are presented as curves of peak section pitching-moment coefficient against Mach number , thickness ratio, and camber.
Book Synopsis Investigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64-210 Airfoil Sections with Various Type Flaps by : James C. Sivells
Download or read book Investigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64-210 Airfoil Sections with Various Type Flaps written by James C. Sivells and published by . This book was released on 1948 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings had zero sweep, an aspect ratio of 9, and a ratio of root to tip chord of 2.5. Wings were tested with and without a representative fuselage and with and without leading-edge roughness.
Book Synopsis Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section by : Boyd C. Myers
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
Book Synopsis A Simple Method for Estimating Terminal Velocity Including Effect of Compressibility on Drag by : Ralph P. Bielat
Download or read book A Simple Method for Estimating Terminal Velocity Including Effect of Compressibility on Drag written by Ralph P. Bielat and published by . This book was released on 1945 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: A generalized drag curve that provides an estimate for the drag rise due to compressibility has been obtained for an analysis of wind-tunnel data of several airfoils, fuselages, nacelles, and windshields at speeds up to and above the wing critical speed. The airfoils analyzed had little or no sweepback and effective aspect ratios above 6.5. A chart based on the generalized drag curve is presented from which the terminal velocity of a conventional airplane that employs a wing of moderate aspect ratio and very little sweepback in a vertical dive may be rapidly estimated. In order to use the chart, the only data that need be known about the airplane are a low-speed drag coefficient, the wing critical speed, and the wing loading. The terminal velocities for three airplanes were computed in order to illustrate the use of the method and chart. Good agreement between the estimated terminal velocity and the measured flight terminal velocity was indicated for all three airplanes.
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 734 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section by : William C. Sleeman
Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Download or read book NACA Research Memorandum written by and published by . This book was released on 19?? with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Approximate Corrections for the Effects of Compressibility on the Subsonic Stability Derivatives of Swept Wings by : Lewis R. Fisher
Download or read book Approximate Corrections for the Effects of Compressibility on the Subsonic Stability Derivatives of Swept Wings written by Lewis R. Fisher and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart for for several aspect ratios and angles of sweep. Lift-curve slopes and values of damping roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data.
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 Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two-dimensional Low-turbulence Pressure Tunnel by : Albert E. Von Doenhoff
Download or read book Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two-dimensional Low-turbulence Pressure Tunnel written by Albert E. Von Doenhoff and published by . This book was released on 1944 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Two low-drag airfoils, the NACA 747A315 and the NACA 747A415, designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient have been tested in the NACA two-dimensional low-turbulence pressure tunnel. Section lift, drag, and pitching-moment coefficients are presented for Reynolds numbers of 3 x 106, 6 x 106, and 9 x 106, together with section lift and section drag data for a Reynolds number of 6 x 106 for the same airfoils with roughened leading edges.
