International Journal of Aerospace Engineering / 2013 / Article / Tab 3 / Research Article
Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing Table 3 Experimental conditions. The Mach sweep is described in Section
3.1 . The pitch pause is described in Section
3.4 . In the pitch pause runs,
represents the values of the first
.
Wind tunnel Designation Model
[deg]
[deg]
[kPa]Re [
] Transonic Case 1 A Mach sweep, 0.9–0.3 0 0 150.5 (
)–151.5 (
) 1.8–0.8 Case 2 A Mach sweep, 1.3–0.6 0 0 150.6 (
)–151.1 (
) 2.0–1.5 Case 3 A 1.0 Pitch pause, 0–4 0 150.5 1.9 Case 4 A 1.1 Pitch pause, 0–4 0 150.3 1.9 Case 5 A 1.2 Pitch pause, 0–4 0 150.6 2.0 Case 6 A 1.3 Pitch pause, 0–4 0 151.0 1.9 Case 7 A 1.0 0 90 150.7 1.9 Case 8 A 1.1 0 90 150.3 1.9 Case 9 A 1.2 0 90 150.6 2.0 Case 10 A 1.3 0 90 150.8 2.0 Supersonic Case 11 A 1.5 Pitch pause, 0–4 0 200.2 2.4 Case 12 A 1.6 Pitch pause, 0–4 0 201.1 2.4 Case 13 A 1.7 0 0 200.5 2.3 Case 14 A 1.7 2 0 201.1 2.3 Case 15 A 1.7 4 0 200.4 2.3 Case 16 A 1.8 Pitch pause, 0–4 0 200.6 2.2 Case 17 A 1.9 Pitch pause, 0–4 0 200.4 2.1 Case 18 A 2.1 Pitch pause, 0–4 0 250.4 2.5 Case 19 A 2.3 0 0 301.4 2.7 Case 20 B 1.5 Pitch pause, 0–4 0 200.7 1.2 Case 21 B 1.6 Pitch pause, 0–4 0 200.7 1.2 Case 22 B 1.7 Pitch pause, 0–4 0 201.4 1.1 Case 23 B 1.8 Pitch pause, 0–4 0 200.2 1.1 Case 24 B 1.9 Pitch pause, 0–4 0 200.0 1.0 Case 25 B 2.0 0 0 249.8 1.3 Case 26 B 2.1 0 0 250.8 1.2
