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 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 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 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 Aerodynamic Characteristics of a Powered Semispan Tilting shrouded propeller VTOL Model in Hovering and Transition Flight written by Kenneth W. Goodson and published by . This book was released on 1962 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: "An investigation of the aerodynamic characteristics of a powered semispan tilting-shrouded-propeller configuration has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 2.67 (based on wing span of 60 inches), a taper ratio of 0.67, and an NACA 2418 airfoil section with a 15-inch-diameter shrouded propeller mounted on the tip. The test results show that large nose-up pitching moments are obtained at transitional speeds of about 40 knots and duct angle of about 70°. Decelerating flight procedures further increases in the nose-up moment. Ground proximity reduces the nose-up pitching moments. The large nose-up moments can be trimmed by use of duct-exit control vanes. The results show that unloading the duct (shroud) by flying at a wing angle of attack of 15° reduces the power required by about 30 percent at 50 knots. Duct-lip stall produces large increases in power required. The results in general show that full-scale aerodynamic simulation can be made with small-scale wind-tunnel models if duct-lip separation at low Reynolds numbers is avoided."--Summary.
Download or read book Investigation of the Aerodynamic Characteristics of a Model Wing propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90 written by John W. Draper and published by . This book was released on 1954 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
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 Effect of Propeller Location and Flap Deflection on the Aerodynamic Characteristics of a Wing propeller Combination for Angles of Attack from 0 to 80 Degrees written by William A. Newsom and published by . This book was released on 1957 with total page 714 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of propeller location and flap deflection on the lift, drag, and pitching-moment characteristics of a wing-propeller combination over an angle-of-attack range from 0 to 80 degrees. The model had four propellers, the slipstream from which covered practically the entire span of the wing. The wing had a 30-percent-chord slotted flap and an 8.5-percent-chord slat. Data were obtained for flap deflections of 0, 20, 40, and 60 degrees with the slat off and on. For one propeller position the power input to the model was measured and tuft studies of the flow on the wing were made. The data are analyzed to assess the feasibility, from consideration of stability and control, of a tilting-wing vertical-take-off-and-landing airplane with the wing pivoted behind the primary wing structure to provide a desirable structural configuration. The main object of the investigation was to determine whether advantage might be taken of the forward shift of the center of gravity of the airplane, as the wing is tilted from an angle of attack of 90 to 0 degrees, to minimize the change in trim pitching moment throughout the transition speed range for such a configuration. The results indicate that with proper propeller position and programming of flap deflection, it is possible to design a configuration of this type in which essentially no change in trim is required throughout the transition from hovering to normal unstalled forward flight.
Download or read book The Effects of Compressibility on the Upwash at the Propeller Planes of a Four engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 written by Armando E. Lopez and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results indicate that for Mach numbers up to 0.60 the upwash angles can be predicted accurately by the available theoretical methods. At Mach numbers above 0.60 the experimental values were less than those predicted by theory and this difference increased with increasing Mach number.
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 Characteristics of a Series of Bodies with and Without Tails at Mach Numbers from 0 8 to 3 0 and Angles of Attack from 0 to 45 Degrees written by Jimmie N. Derrick and published by . This book was released on 1976 with total page 896 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted in a 16 ft. transonic tunnel, a supersonic tunnel, A and a trisonic tunnel to establish a bank of systematic data for body and body-tail configurations at high angles of attack. The configurations were tested at Mach numbers between 0.8 and 3.0, angles of attack from -2 to 45 degrees, and roll angles from 0 to 90 degrees. The aerodynamic characteristics were obtained for the total configuration as well as each of the four undeflected tail fins.
Download or read book The Effect of Simulated Icing on Propeller Performance written by Blake W. Corson and published by . This book was released on 1946 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests of a 10-foot-diameter three-blade Curtiss 89301-15 propeller with Clark Y blade sections have been conducted in the Langley 16-foot high-speed tunnel in order to determine the effect of simulated iceon the aerodynamic characteristics of the propeller. The irregular coat of cement and fabric was used on the blades to simulate in outline and thickness a formation of glaze ice that might be formed in flight. The propellers were tested on a new 2000-horsepower dynamometer, a brief description of which is included. All tests were made at a rotational speed of 1800 rpm for blade angles of 20, 25, 35, and 40 degrees at the 42-inch radius and at airspeeds varying from 120 to 420 miles per hour. The results are representative of full-scale constant-speed propeller operation.
Download or read book Rotor body Aerodynamic Interactions written by Mark D. Betzina and published by . This book was released on 1983 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was conducted in which independent, steady-state aerodynamic forces and moments were measured on a 2.24-m-diam, two- bladed helicopter rotor and on several different bodies. The objective was to determine the mutual interaction effects for variations in velocity, thrust, tip-path-plane angle of attack, body angle of attack, rotor/body position, and body geometry. the results of the investigation show that the body longitudinal aerodynamic characteristics are significantly affected by the presence of a rotor and hub, and that the hub interference may be a major part of such interaction. This report presents the effects of various parameters on the interactions and discusses the difficulties encountered in determining the effect of the body on the rotor performance.
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and Naca 65a004 Airfoil Sections written by JACK F. RUNCKEL and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
Download or read book Investigation of the Aerodynamic Characteristics of a Model Wing Propeller Combination and of the Wing and Propeller Separately at Angles of Attack U P to 90 written by Richard E. Kuhn and published by . This book was released on 1956 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
