Topic
Pitching moment
About: Pitching moment is a research topic. Over the lifetime, 3213 publications have been published within this topic receiving 38721 citations.
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01 Feb 1956
TL;DR: In this paper, the NACA 0011 airfoil in icing was measured using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes.
Abstract: Report presenting measurements of lift, drag, and pitching moment of an NACA 0011 airfoil in icing using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes. Results regarding the airfoil characteristics with the de-icer operating and effect of primary ice formation on drag, lift, and pitch with the de-icer inoperative are provided.
28 citations
01 Dec 1980
TL;DR: In this article, wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications.
Abstract: Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
28 citations
28 citations
TL;DR: In this article, the authors investigated the aerodynamic properties of the Ahmed body at varying Reynolds numbers under yawing conditions and found that the lift and the pitching moment exhibit strong fluctuations due to bi-stable flow around a critical angle β of ±12.5°.
28 citations
22 Jun 2015
TL;DR: In this article, the aerodynamic environment of a high speed coaxial compound helicopter in steady level forward flight using CFD-CSD coupling is examined, and the model is validated using public-domain information and flight test data obtained for the Sikorsky X2 Technology Demonator.
Abstract: This paper examines the aerodynamic environment of a high speed coaxial compound helicopter in steady level forward flight using CFD-CSD coupling. Numerical simulations have been performed to study trim configurations of an eight-bladed coaxial compound configuration (four blades per rotor) using comprehensive analysis coupled to a vortex wake model. The model is validated using public-domain information and flight test data obtained for the Sikorsky X2 Technology Demonstrator. Rotor-rotor interference follows the expected momentum theory type model, with the lower rotor experiencing larger induced inflow. Thrust sharing between rotors remains nominally constant, with at most ±5% bias over the speed range studied. CFD analysis for the rotors is then introduced at select forward flight speeds to identify key aerodynamic modeling refinements. In particular, impulsive normal force due to rotor blade crossings are not captured accurately by the vortex wake model. The impulsive 8/rev pitching moment is completely missed by the reduced order model. While significant, this aerodynamic pitching moment does not excite a noticeable torsion response from the stiff rotor considered. For future designs with lower stiffness blades, these impulsive airloads may induce additional vibratory hub loads and drive the design of the rotor pitch control system.
27 citations