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.
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.
Download or read book The Effects of Compressibility on the Lift Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections written by Morton Cooper and published by . This book was released on 1948 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of tests of a 12-foot-span tapered wing of NACA 66-series sections at Mach numbers up to 0.69 indicated that the maximum lift coefficient varied appreciably with Mach number and was affected to a marked extent by the sharpness of the lending edge at the higher Mach numbers. No significant changes in span load distributions occurred through the Mach number range for all angles of attack below the stall. The formation of extensive local supersonic-flow regions caused the center of pressure to move forward at high angles of attack and high Mach numbers.
Download or read book Effects of Compressibility on Normal force Pressure and Load Characterstics of a Tapered Wing of NACA 66 series Airfoil Sections with Split Flaps written by F. E. West and published by . This book was released on 1948 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of compressibility on the normal-force, pressure, and load characteristics of a 12-foot tapered wing of NACA 66-series airfoil sections equipped with split flaps is presented for Mach numbers up to 0.585 and an angle-of-attack range of -4 degrees through the stall. Both 55-percent-span and 98-percent-span split flaps deflected 60 degrees and having chords of 20-percent of the wing chord were tested.
Download or read book The Effect of Compressibility on the Lift Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections written by Morton Cooper and published by . This book was released on 1948 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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.
Download or read book Effects of Mach Number Variation Between 0 07 and 0 34 and Reynolds Number Variation Between 970 000 and 8 100 000 on the Maximum Lift Coefficient of a Wing of NACA 64 210 Airfoil Sections written by James E. Fitzpatrick and published by . This book was released on 1952 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested with and without partial-span and full-span slip flaps deflected 60 degrees. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration.
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 Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Download or read book Effects of Compressibility on Normal force Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections with Split Flaps written by F. E. West and published by . This book was released on 1948 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Compressibility on Maximum Lift Coefficients for Six Propeller Airfoils written by Harold E. Cleary and published by . This book was released on 1945 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extension of previously reported data on the variation of lift coefficient with Mach number, camber, and thickness ratio is presented. The data were obtained from pressure-distribution tests in the Langley 8-foot high-speed tunnel of six propeller airfoils of 1-foot chord.
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.
Download or read book A Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 653 418 written by John H. Quinn and published by . This book was released on 1944 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation in two NACA wind tunnels has determined the effect of Reynolds number and stream turbulence on the lift and drag characteristics of a low-drag airfoil, the NACA 653-418, a=1.0 section, particularly at low Reynolds numbers, to give an indication of the performance of low-drag wings in low-scale tests. The results are correlated with similar data for the same airfoil section in the NACA two-dimensional low-turbulence pressure tunnel to provide data over a range of Reynolds number from 0.19 to 9.0 x 106. Large increases in minimum drag coefficient were found as the Reynolds number decreased. This effect was particularly marked at Reynolds numbers below 1.5 x 106. At Reynolds numbers below 1.5 x 106, stream turbulence had little effect on the drag characteristics of the NACA 653-418 airfoil section when compared on the basis of test Reynolds number but, at higher Reynolds numbers, stream turbulence had a detrimental effect on drag. Large decreases in maximum lift coefficient were found with decreasing Reynolds number; most of this decrease was encountered at Reynolds numbers above 2.0 x 106. Marked differences in maximum lift were apparent between the results obtained at high and low turbulence. When compared on the basis of effective Reynolds number, however, fair agreement was reached between the data obtained under both turbulence conditions.
Download or read book Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small scale Model at High Subsonic Speeds written by Albert G. Few and published by . This book was released on 1954 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
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.
Download or read book The Effects of Amount and Type of Camber on the Variation with Mach Number of the Aerodynamic Characteristics of a 10 percent thick NACA 64A series Airfoil Section written by James L. Summers and published by . This book was released on 1950 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of variation of amount and type of camber on the variation with Mach number of the aerodynamic characteristics of 10-percent-chord-thick NACA 64A-series airfoil sections are evaluated from tests in the Ames 1- by 3-1/2-foot high-speed wing tunnel at Mach numbers of 0.3 to 0.9 and corresponding Reynolds numbers from 1,000,000 to 2,000,000. Lift, drag, and pitching-moment characteristics were determined for airfoil sections having values of design section lift coefficient of 0 and 0.3, 0.6, and 0.9 with NACA a=1.0 mean line, and 0.3, 0.6 with the NACA a=0.4 mean line.
Download or read book Compressibility Effects on the Longitudinal Stability and Control of a Pursuit type Airplane as Measured in Flight written by William N. Turner and published by . This book was released on 1945 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of the longitudinal stability and control of a pursuit-type airplane (the P-39N-1 airplane) were made in flight up to a Mach number of 0.78. The data are presented in the form of curves showing the variation, with center-of-gravity position, dynamic pressure, and Mach number, of the stick-fixed and stick-free stability, control, and balance of the airplane.
