Journal of the American Helicopter Society (J AM HELICOPTER SOC )

Publisher: American Helicopter Society

Journal description

Current impact factor: 0.63

Impact Factor Rankings

2015 Impact Factor Available summer 2015
2013 / 2014 Impact Factor 0.627
2012 Impact Factor 0.514
2011 Impact Factor 0.549
2010 Impact Factor 0.393
2009 Impact Factor 0.254
2008 Impact Factor 0.467
2007 Impact Factor 0.426
2006 Impact Factor 0.575
2005 Impact Factor 0.443
2004 Impact Factor 0.464
2003 Impact Factor 0.474
2002 Impact Factor 0.59
2001 Impact Factor 0.469
2000 Impact Factor 0.273
1999 Impact Factor 0.493
1998 Impact Factor 0.329
1997 Impact Factor 0.655
1996 Impact Factor 0.5
1995 Impact Factor 0.116
1994 Impact Factor 0.114
1993 Impact Factor 0.364
1992 Impact Factor 0.464

Impact factor over time

Impact factor
Year

Additional details

5-year impact 0.57
Cited half-life 0.00
Immediacy index 0.07
Eigenfactor 0.00
Article influence 0.30
Website Journal of the American Helicopter Society website
Other titles Journal of the American Helicopter Society
ISSN 0002-8711
OCLC 1827576
Material type Periodical
Document type Journal / Magazine / Newspaper

Publications in this journal

  • [Show abstract] [Hide abstract]
    ABSTRACT: The unsteady flow around the pitching helicopter main rotor blade airfoil EDI-M109 was experimentally investigated at conditions similar to those existing on a retreating rotor blade in forward flight. High speed pressure measurements and hot film anemometry were used to investigate the unsteady transition characteristics of the airfoil. Results are presented for dynamic test points with attached flow, light dynamic stall and deep dynamic stall at M = 0.3 and Re = 1.8 x 10^6. The results include the discussion of the periodicity of the hot film signals for different flow states. The transition process of the pitching airfoil is analyzed and the significance of the intermittent region is described. A time delay between the transition and the model motion is discussed and a linear relationship between the transition position and the time is observed. The influences of the pitching amplitude on the transition characteristics are discussed and the flow separation initiating dynamic stall is analyzed.
    Journal of the American Helicopter Society 01/2014; 59(1):1-12.
  • [Show abstract] [Hide abstract]
    ABSTRACT: Anthropometric test devices (ATDs), commonly referred to as crash test dummies, are effective tools used to conduct aerospace safety evaluations. In this study, the latest finite element (FE) model of the Test Device for Human Occupant Restraint (THOR) dummy was simulated under vertical impact conditions based on data recorded in a series of drop tests conducted at the NASA Langley Research Center (LaRC). The purpose of this study was threefold. The first was to improve and then evaluate this FE model for use in a vertical loading environment through kinematic and kinetic response comparisons. The second was to evaluate dummy injury criteria under variable impact conditions. The last was to determine the response sensitivity of the FE model with respect to its pre-impact postural position. Results demonstrate that the updated FE model performs well under vertical loading and predicts injury criteria values close to those recorded in testing. In the postural sensitivity study, the head injury criteria (HIC) response and peak lumbar load (LL) show to be primarily sensitive to the pre-impact head angle and thorax angle, respectively. The promising results shown by the dummy model recommends its use in impact simulations with vertical deceleration pulses close to those used in this study. In addition, it is believed that assigning accurate viscoelastic material properties to the deformable parts of the model may further increase the model fidelity for a larger range of impacts.
    Journal of the American Helicopter Society 01/2014;
  • [Show abstract] [Hide abstract]
    ABSTRACT: The experimental investigation of constant blowing air jets as fluidic control devices for helicopter dynamic stall control is described. A carbon fiber airfoil of constant OA209 cross section was fitted with a pneumatic system to deliver dry compressed air as jets for flow control at total pressures of up to 10 bar. The experiment used porthole jets of radius 1% chord, positioned at 10% chord and with spacing 6.7% chord. The positive dynamic stall control effects were demonstrated at Mach 0.3, 0.4, and 0.5 for deep dynamic stall test cases with the best test cases reducing the pitching moment peak after the main stall by 83% while increasing the mean lift over one pitching cycle by 30%. The conclusions from the experiments are supported by three-dimensional unsteady Reynolds-averaged Navier–Stokes (URANS) computations of the pitching airfoil with flow control using the DLR-TAU code.
    Journal of the American Helicopter Society 10/2013; 58(4).
  • Journal of the American Helicopter Society 10/2013; 58(4).
  • [Show abstract] [Hide abstract]
    ABSTRACT: The flow over an OA209 airfoil subjected to a sinusoidal pitching motion under dynamic stall conditions and equipped with an innovative Deployable Vortex Generator actuator inducing stall control is experimentally and numerically investigated. Pressure and TR-PIV measurements allow a detailed comparison to be performed between clean and controlled cases, including separation point detection and Proper Orthogonal Decomposition analysis. Along with wind tunnel testing, numerical simulations are performed by solving the Unsteady RANS equations with the ONERA elsA code. Computations are successfully compared to the experimental reference and bring further understanding of the Deployable Vortex Generator actuation.
    Journal of the American Helicopter Society 07/2013; Vol. 58(2013-3):1-13.
  • [Show abstract] [Hide abstract]
    ABSTRACT: A computational investigation of the effect of rotation on two-dimensional (2D) deep dynamic stall has been undertaken, showing that the effect of rotation is to reduce the severity of the pitching moment peak and cause earlier reattachment of the flow. A generic single blade rotor geometry was investigated, which had a pitching oscillation around the quarter chord axis while in hover, causing angle-driven dynamic stall. The results at the midpoint of the blade have the same Mach number (0.31), Reynolds number (1.15×106), and pitching motion (α =13◦±7◦) as a dynamic stall test case for which significant experimental wind tunnel data and 2D computations exist. The rotating blade is compared with 2D computations and computations using the same blade without rotation at Mach 0.31 and with the same pitching motion. All test cases involve geometries propagating into undisturbed flow with no downwash. The three-dimensional (3D) grid computed without rotation had lower lift at the reference section than for a 2D computation with the same geometric angle of attack time history, and the lift overshoot classically observed for Spalart–Allmaras turbulence models during 2D dynamic stall was significantly reduced in the 3D case. Rotation reduced the strength of the dynamic stall vortex, which reduced the accompanying pitching moment peak by 25%.
    Journal of the American Helicopter Society 07/2013; 58(3):1-9.
  • Journal of the American Helicopter Society 07/2013; 58(3):1-13.
  • Journal of the American Helicopter Society 04/2013; 58(2):1-9.
  • [Show abstract] [Hide abstract]
    ABSTRACT: Flight testswith a German Army SikorskyCH-53G helicopter were performed to evaluate the applicability and repeatability of the U.S. Army’s Aeronautical Design Standard (ADS)-33E-PRF cargo helicopter handling qualities requirements. The objectives were to corroborate earlier findings and to propose modifications if deemed necessary. The CH-53G was chosen because it is the largest helicopter operated by the German Army, and its dedicated role is cargo and troop transport. The quantitative criteria and the associated boundaries as specified in the standard were largely confirmed. Several flight test maneuvers were revised and tailored. Generally, the heights for performing the near-earth maneuvers were increased. The time/tolerances experienced were borderline desired/adequate or adequate.
    Journal of the American Helicopter Society 01/2013; 58(2013-01-01-1):1-11.
  • Journal of the American Helicopter Society 10/2012; 57(4).
  • Journal of the American Helicopter Society 04/2012;