- •Laboratory work.
- •Critical Mach number models of straight and sweep-back wings determination
- •Necessary theoretical information and relations/
- •Fig. 1. Schemes of the flow around thin and thick aerodynamic profile.
- •The order of fulfilling laboratory work.
- •Fig. 6. Chart of realization of experiment (view from above)
Fig. 6. Chart of realization of experiment (view from above)
1 – nozzle of wind tunnel, 2 is a model of wing, 3 is crossing the drainage holes is located in that, 4 is a diffuser of wind tunnel, 5 is a limb for counts of angle of values, 6 is basis of holder, is a corner of sweep back angle of leading edges.
point |
c,mm= |
145 |
|
alpha,deg= |
0 |
|
al, deg= 45 |
number |
x,mm |
y,mm |
hIIR - hIIL |
hIR - hIL |
xrel |
yrel |
cpi |
1 |
5 |
7 |
80 |
312 |
0,034483 |
0,048276 |
0,25641 |
2 |
15 |
12 |
-68 |
307 |
0,103448 |
0,082759 |
-0,2215 |
3 |
30 |
15 |
-95 |
294 |
0,206897 |
0,103448 |
-0,32313 |
4 |
50 |
16 |
-101 |
309 |
0,344828 |
0,110345 |
-0,32686 |
5 |
75 |
14 |
-70 |
309 |
0,517241 |
0,096552 |
-0,22654 |
6 |
100 |
12 |
-52 |
311 |
0,689655 |
0,082759 |
-0,1672 |
7 |
125 |
6 |
-18 |
310 |
0,862069 |
0,041379 |
-0,05806 |
8 |
10 |
-4 |
-95 |
295 |
0,068966 |
-0,02759 |
-0,32203 |
9 |
30 |
-4,1 |
-29 |
305 |
0,206897 |
-0,02828 |
-0,09508 |
10 |
50 |
-4,5 |
-23 |
309 |
0,344828 |
-0,03103 |
-0,07443 |
11 |
75 |
-3 |
-35 |
314 |
0,517241 |
-0,02069 |
-0,11146 |
12 |
100 |
-2 |
-6 |
304 |
0,689655 |
-0,01379 |
-0,01974 |
13 |
125 |
-1 |
9 |
312 |
0,862069 |
-0,0069 |
0,028846 |
|
|
|
|
|
|
min cpi |
-0,32686 |
0 |
0 |
1 |
|
|
|
|
|