Three 50% flap configurations located inboard, outboard, and at midsemispan position were tested through momentum coefficient range from 0 to about 10 and angle of attack range from 10 to 28°; corresponding flow field characteristics are presented for longitudinal tail position of 4 wing chords behind trailing edge of wing through range of tail-height locatons of plus or minus 2 chords.
Low-speed wind-tunnel investigation of reflection plane wing model equipped with partial-span jet-augmented flaps
NASA -- Tech Note
1961
53 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Wind-tunnel investigation of tapered wings with ordinary ailerons and partial-span split flaps
Engineering Index Backfile | 1937
|Wind-tunnel investigation of tapered wings with ordinary ailerons and partial-span split flaps
Engineering Index Backfile | 1937
|Wind-tunnel investigation of tapered wings with ordinary ailerons and partial-span split flaps
Engineering Index Backfile | 1937
|