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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Wing-flow tests of a triangular wing of aspect ratio two I : effectiveness of several types of trailing-edge flaps on flat-plate models

Wing-flow tests of a triangular wing of aspect ratio two I : effectiveness of several types of trailing-edge flaps on flat-plate models

Date: November 14, 1947
Creator: Rathert, George A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees

Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees

Date: June 7, 1949
Creator: Schneiter, Leslie E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Date: November 29, 1949
Creator: Johnson, Harold S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Date: December 10, 1947
Creator: Salmi, Reino J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Date: November 8, 1948
Creator: Salmi, Reino J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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