02221cam a2200433Ii 4500011426061MiAaHDL20141013010000.0m d cr bn ---auaua780303s1977 dcua b f000 0 eng d7252158219770022140N772908477N29084sdr-uiuc6363559(OCoLC)368691522161GPOGPOABCOCLCQFERUIUUTL521.3.T4A3 no. 3533NAS 1.15:X-3533L-11459Blair, A. B.Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 /A.B. Blair, Jr.Washington :National Aeronautics and Space Administration ;Springfield, Va. :For sale by the National Technical Information Service,1977.95 p. :ill. ;27 cm.NASA technical memorandum ; NASA TM X-3533Issued Aug. 1977.Includes bibliographical references.An experimental wind tunnel investigation has been made to determine the longitudinal and lateral aerodynamic stability and control characteristics of two tail fin arrangements of a monowing missile model. Both a conventional cruciform and a low profile tail arrangement were tested. The results indicate that the tail surfaces of both configurations were effective in producing pitch control. It was also concluded that both are effective in producing roll and yaw control that is accompanied by proverse yaw and roll, respectively. The conventional cruciform tail produces the most roll and yaw control.Mode of access: Internet.Supersonic wind tunnels.nasatSupersonic speeds.nasatLift drag ratio.nasatControl stability.nasatTail assemblies.nasatMissile design.nasatAerodynamic characteristics.nasatGuided missilesControl systems.United States.National Aeronautics and Space Administration.01142606120101006153547.020141013010000.020141112173021.02025-01-02T19:04:04Z2025-01-02T18:30:02ZSDR-UIUCUNKNOWNloader.pl-003-020BKsdr-uiuc6363559uiugSDRUIUCuiug.30112106722256UIU6363559UIUUIUC20250102googleuiug.301121067222561977pdbibUS fed doc--NTIS: pubdate < 2020