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Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98
Language: en
Pages: 76

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98

Authors: F. E. West
Categories:
Type: BOOK - Published: 1960 - Publisher:

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Effect of Body-Mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Deg Swept Wing at Mach Numbers from 0.80 to 0.98
Language: en
Pages: 80

Effect of Body-Mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Deg Swept Wing at Mach Numbers from 0.80 to 0.98

Authors:
Categories:
Type: BOOK - Published: 1960 - Publisher:

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The Journal of the Royal Aeronautical Society
Language: en
Pages: 972

The Journal of the Royal Aeronautical Society

Authors: Royal Aeronautical Society
Categories: Aeronautics
Type: BOOK - Published: 1961 - Publisher:

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Investigation of Spoiler Ailerons for Use as Speed Brakes Or Glide-path Controls on Two NACA 65-series Wings Equipped with Full-span Slotted Flaps
Language: en
Pages: 68

Investigation of Spoiler Ailerons for Use as Speed Brakes Or Glide-path Controls on Two NACA 65-series Wings Equipped with Full-span Slotted Flaps

Authors: Jack Fischel
Categories: Aerofoils
Type: BOOK - Published: 1949 - Publisher:

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Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency operatiion of airplanes. These speed brakes or glide-path co
Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01
Language: en
Pages: 52

Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01

Authors: Douglas R. Lord
Categories: Aerodynamics
Type: BOOK - Published: 1957 - Publisher:

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An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characterist