Wind Tunnel Investigation At Mach Numbers From 1 90 To 2 86 Of A Canard Controlled Missile With Ram Air Jet Spoiler Roll Control

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NASA SP.

Anonim
NASA SP Book PDF

Author : Anonim
Publisher : Unknown
Page : 396 pages
File Size : 55,7 Mb
Release : 1962
Category : Aeronautics
ISBN : UOM:39015040281498

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NASA SP. by Anonim Pdf

Government Reports Announcements & Index

Anonim
Government Reports Announcements Index Book PDF

Author : Anonim
Publisher : Unknown
Page : 1352 pages
File Size : 53,7 Mb
Release : 1978-07
Category : Science
ISBN : CORNELL:31924055260859

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Government Reports Announcements & Index by Anonim Pdf

Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail

Paul T. Soderman,Thomas N. Aiken
Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail Book PDF

Author : Paul T. Soderman,Thomas N. Aiken
Publisher : Unknown
Page : 108 pages
File Size : 42,5 Mb
Release : 1971
Category : Airplanes
ISBN : UIUC:30112106692574

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Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail by Paul T. Soderman,Thomas N. Aiken Pdf

The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.

Wind-tunnel Investigation at High Subsonic Speeds of the Effect of Spoiler Profile on the Lateral Control Characteristics of a Wing-fuselage Combination Winter Quarter-chord Line Swept Back 32.6© and NACA 65A006 Airfoil Section

Harold S. Johnson
Wind tunnel Investigation at High Subsonic Speeds of the Effect of Spoiler Profile on the Lateral Control Characteristics of a Wing fuselage Combination Winter Quarter chord Line Swept Back 32 6 and NACA 65A006 Airfoil Section Book PDF

Author : Harold S. Johnson
Publisher : Unknown
Page : 20 pages
File Size : 41,6 Mb
Release : 1953
Category : Airplanes
ISBN : UOM:39015095100718

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Wind-tunnel Investigation at High Subsonic Speeds of the Effect of Spoiler Profile on the Lateral Control Characteristics of a Wing-fuselage Combination Winter Quarter-chord Line Swept Back 32.6© and NACA 65A006 Airfoil Section by Harold S. Johnson Pdf

Wind-tunnel Study of Slot Spoilers for Direct Lift Control

Dominick Andrisani (II.),Garl L. Gentry (Jr.),Joseph W. Stickle
Wind tunnel Study of Slot Spoilers for Direct Lift Control Book PDF

Author : Dominick Andrisani (II.),Garl L. Gentry (Jr.),Joseph W. Stickle
Publisher : Unknown
Page : 52 pages
File Size : 42,8 Mb
Release : 1972
Category : Lift (Aerodynamics)
ISBN : UIUC:30112106883074

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Wind-tunnel Study of Slot Spoilers for Direct Lift Control by Dominick Andrisani (II.),Garl L. Gentry (Jr.),Joseph W. Stickle Pdf

An investigation was conducted in a 300-mph 7- by 10- foot tunnel to obtain data for a slot spoiler direct lift control system. Slot spoilers are believed to have advantages over flap-type direct lift control (DLC) systems because of the small amount of power required for actuation. These tests, run at a Reynolds number of 1,400,000 showed that up to 78 percent of the lift due to flap deflection could be spoiled by opening several spanwise slots within the flaps. For a given lift change the drag change was significantly less than that which would be obtained by a variable flap DLC system. A nozzle-shaped slot was the most effective of the slot shapes tested.

Free-flight Measurements of the Rolling Effectiveness and Drag of Trailing-edge Spoilers on a Tapered Sweptback Wing at Mach Numbers Between 0.6 and 1.4

Eugene D. Schult,E. M. Fields
Free flight Measurements of the Rolling Effectiveness and Drag of Trailing edge Spoilers on a Tapered Sweptback Wing at Mach Numbers Between 0 6 and 1 4 Book PDF

Author : Eugene D. Schult,E. M. Fields
Publisher : Unknown
Page : 18 pages
File Size : 47,9 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015095100775

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Free-flight Measurements of the Rolling Effectiveness and Drag of Trailing-edge Spoilers on a Tapered Sweptback Wing at Mach Numbers Between 0.6 and 1.4 by Eugene D. Schult,E. M. Fields Pdf