02876nam a2200409Ia 4500102892739MiAaHDL20250726000000.0m d cr bn ---auaua210610s1984 ohua b f000 0 eng d(MiU)99187625246306381sdr-miu.99187625246306381(OCoLC)1255716783(GWLA)gwla on1255716783TRAALengTRAALMAIND 301.45/57:84-3109Miller, L. Earl,author.Post stall maneuvers and thrust vectoring performance analysis /L. Earl Miller.Wright-Patterson Air Force Base, Ohio :Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force,1984.x, 67 pages :illustrations ;28 cm.texttxtrdacontentunmediatednrdamediavolumencrdacarrierAFWAL-TR (Air Force Wright Aeronautical Laboratories) ;84-3109"Final Technical Report August 83 - July 1984,""July 1984."Includes bibliographical references (page 38)The purpose of this effort was to determine whether or not there are any apparent performance improvements through Post Stall Maneuvers (PSM) or thrust vectoring. PSM is a result of high angles of attack, greater than the stall value. Two different problems were addressed. The first examined instantaneous turning performance. The second focused on minimum time turn problems. The impact of both vectored and nonvectored thrust was considered. It was proven that minimum time turns fall in the vertical plane. For maximum instantaneous turning rate and nonvectored thrust high angle of attack results if the speed is less than the critical speed which is approximately Mach 0.2. The optimal angle of attack approaches ninety degrees as the speed approaches zero. For vectored thrust, the stall angle of attack is optimum and the thrust vector angle is the complement of the angle of attack. PSM is not optimal if thrust vectoring is available. For minimum time turning performance, maximum thrust is optimal. At the end of the trajectory, the optimal angle of attack equals that for maximum instantaneous performance. PSM is optimal. As the thrust to weight ratio increases, the maximum angle of attack increases.Mode of access: Internet.Aerodynamics.AirplanesPerformance.AirplanesMotorsThrust.Stalling (Aerodynamics)Air Force Wright Aeronautical Laboratories,issuing body.Air Force Flight Dynamics Laboratory (U.S.),sponsor.Technical Report Archive & Image Library (TRAIL)3901509532161110289273920220802101946.020250726000000.020260226165640.02026-02-27T09:52:06Z2024-08-02T17:30:02ZSDR-MIUmiuALMAprepare.pl-004-009BKsdr-miu.99187625246306381MiUSDRGWLAmdp.39015095321611MIU99187625246306381MIUGWLA20260227googlemdp.390150953216111984pdbibUS fed doc