Download or read book Aerodynamic Loads on an Isolated Shrouded propeller Configuration of Angles of Attack from 10 Degrees to 110 Degrees written by Kalman J. Grunwald and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Loads on an Isolated Shrouded propeller Configuration for Angles of Attack from 10 Degrees to 110 Degrees written by KALMAN J. GRUNWALD and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the division of loads between the propeller and the shroud of a shroudedpropeller configuration was conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. This investigation covered an angle-of-attack range from -10 to 110 degrees and a range of advance ratios (0 to 0.595) typical of the transition speed range of a tilt-duct VTOL aircraft. For the configurations with fixed blade angle (24 degrees at the three-quarter radius), the normal force and pitching moment developed by the propeller and spinner were only a relatively small part of the over-all normal force and pitching moment of either a stalled or an unstalled shroud. The ratio of the thrust of the propeller and spinner to total thrust was found to vary from about 0.4 in hovering to about 0.7 at the highest advance ratio of the tests, 0.595, with the shroud at zero angle of attack. (Author).
Download or read book U S Government Research Reports written by and published by . This book was released on 1962 with total page 1166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advances in Computational Methods and Technologies in Aeronautics and Industry written by Dietrich Knoerzer and published by Springer Nature. This book was released on 2022-12-12 with total page 290 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides research results using computational methods for fluid dynamics and engineering problems in aeronautics and other scientific and industrial applications. It gives an overview on the state of the art and the technology trends requiring advanced computational methods towards digitization in industrial and scientific processes. The chapters are based on Special Technology Sessions of the WCCM-ECCOMAS Virtual Congress 2021.
Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1962 with total page 1170 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book USAF Stability and Control Datcom written by Douglas Aircraft Company and published by . This book was released on 1975 with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index Aeronauticus written by and published by . This book was released on 1962 with total page 816 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Wind tunnel Tests to a Mach Number of 0 90 of a Four engine Propeller driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 written by George G. Edwards and published by . This book was released on 1956 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
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 Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 to 180 Degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the aerodynamic characteristics of a four-blade rigid model propeller has been conducted in the Langley full-scale tunnel for angles of attack from 0 to 180 degrees, blade angles from 0 to 67.5 degrees, and a range of advance ratio from 0 to 6.2. The investigation included a preliminary exploration of vertical descent and a comparison with theory of the rate of change of the normal-force coefficient with angle of attack and of the aerodynamic characteristics of the propeller at zero angle of attack.
Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 degree to 180 degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Shrouded Propeller Investigations Wind Tunnel Tests of a 4 bladed Shrouded Propeller Model Having a 0 4 Hub tip Diameter Ratio Centerbody written by VERNON O. HOEHNE and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests have been conducted on a shrouded propeller model with four variable pitch blades operating within a 0.50 chord/diameter ratio shroud and having a 0.4 hub/tip diameter ratio centerbody. The shroud had provisions for changing the inlet configuration from a streamlined or high-speed shape to a flared or bellmouth shape and for mounting either a diffused or nondiffused exit. Seven exit vanes designed to remove the rotational component of jet velocity at design conditions were installed. The design of the propeller blades was identical to the design of the blades used in a model having a 0.3 hub/tip dia eter ratio centerbody. A comparison of the test data from these two models shows the effect of centerbody size on shrouded propeller performance. Performance of the model was measured throughout a range of advance ratios from zero to 2.2 at several blade pitch settings and angles of attack between zero and 90 degrees. Results are presented in the form of force and moment coefficients varying with power coefficient for forward flight conditions and with propeller rotation speed and static disc loading at zero speed conditions. (Author).
Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 degree to 180 degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamics of V STOL Flight written by Barnes Warnock McCormick and published by Courier Corporation. This book was released on 1999-01-01 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extremely practical overview of V/STOL (vertical/short takeoff and landing) aerodynamics, this volume offers a presentation of general theoretical and applied aerodynamic principles, covering propeller and helicopter rotor theory for both the static and forward flight cases. Both a text for students and a reference for professionals, the book can be used for advanced undergraduate or graduate courses. Numerous detailed figures, plus exercises. 1967 edition. Preface. Appendix. Index.
Download or read book Marine Propellers and Propulsion written by John Carlton and published by Butterworth-Heinemann. This book was released on 2012-10-30 with total page 539 pages. Available in PDF, EPUB and Kindle. Book excerpt: The early development of the screw propeller. Propeller geometry. The propeller environment. The ship wake field, propeller performance characteristics.
Download or read book Introduction to autogyros helicopters and other V STOL aircraft written by Franklin D. Harris and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Sound Measurements for Five Shrouded Propellers at Static Conditions written by Harvey H. Hubbard and published by . This book was released on 1950 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sound-pressure measurements are reported for five shrouded propellers and are compared with those for an unshrouded propeller operating at approximately the same rotational speed and power. The maximum total sound pressure produced by a two-blade shrouded propeller is found to vary approximately from one-half to twice as much as that for an unshrouded two-blade propeller, depending on whether the flow at the shroud surface is unseparated or separated, respectively. Shroud chord is found not to be critical except insofar as the areodynamic considerations are affected. In general, if the shroud-propeller unit satisfies aerodynamic requirements, good sound characteristics will also be obtained.
