Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86

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050 ⊔ 4 ‡aTL521.3.T4 ‡bA3 no. 3533
086 0 ⊔ ‡aNAS 1.15:X-3533
088 ⊔ ⊔ ‡aL-11459
100 1 ⊔ ‡aBlair, A. B.
245 1 0 ‡aStability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 / ‡cA.B. Blair, Jr.
260 ⊔ ⊔ ‡aWashington : ‡bNational Aeronautics and Space Administration ; ‡aSpringfield, Va. : ‡bFor sale by the National Technical Information Service, ‡c1977.
300 ⊔ ⊔ ‡a95 p. : ‡bill. ; ‡c27 cm.
490 0 ⊔ ‡aNASA technical memorandum ; NASA TM X-3533
500 ⊔ ⊔ ‡aIssued Aug. 1977.
504 ⊔ ⊔ ‡aIncludes bibliographical references.
520 ⊔ ⊔ ‡aAn 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.
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 7 ‡aSupersonic wind tunnels. ‡2nasat
650 ⊔ 7 ‡aSupersonic speeds. ‡2nasat
650 ⊔ 7 ‡aLift drag ratio. ‡2nasat
650 ⊔ 7 ‡aControl stability. ‡2nasat
650 ⊔ 7 ‡aTail assemblies. ‡2nasat
650 ⊔ 7 ‡aMissile design. ‡2nasat
650 ⊔ 7 ‡aAerodynamic characteristics. ‡2nasat
650 ⊔ 0 ‡aGuided missiles ‡xControl systems.
710 1 ⊔ ‡aUnited States. ‡bNational Aeronautics and Space Administration.
CID ⊔ ⊔ ‡a011426061
DAT 0 ⊔ ‡a20101006153547.0 ‡b20141013010000.0
DAT 1 ⊔ ‡a20141112173021.0 ‡b2025-01-02T19:04:04Z
DAT 2 ⊔ ‡a2025-01-02T18:30:02Z
CAT ⊔ ⊔ ‡aSDR-UIUC ‡dUNKNOWN ‡lloader.pl-003-020
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