Selected Data on Supersonic Engines
From NASA AIAA 92-1027 TBE
| Design Mach |
1.6 |
2 |
2.4 |
| SLSThrust (klb) |
70.6 |
69 |
65.5 |
| Engine Weight |
9252 |
9278 |
9587 |
| Total Weight |
14595 |
15521 |
17424 |
| Cruise sfc |
1.118 |
1.199 |
1.31 |
Some thrust and sfc lapse rates: (From 92-1027, Concorde brochure, Boeing CR, SAE901890, SAE1892 )
| M |
h |
T |
sfc |
eta |
source |
| 0 |
0 |
70610 |
0.8746 |
0 |
AIAA92-1027 |
| 1.6 |
45000 |
29528 |
1.118 |
0.346 |
|
| |
|
|
|
|
|
| 0 |
0 |
69035 |
0.8728 |
0 |
AIAA92-1027 |
| 2 |
55000 |
21911 |
1.1991 |
0.404 |
|
| |
|
|
|
|
|
| 0 |
0 |
65482 |
0.9293 |
0 |
AIAA92-1027 |
| 2.4 |
65000 |
18955 |
1.31 |
0.443 |
|
| |
|
|
|
|
|
| 0 |
0 |
38050 |
|
|
Concorde Brochure |
| 2 |
60000 |
6791 |
-- |
|
|
| |
|
|
|
|
|
| 0 |
0 |
52730 |
-- |
0 |
Boeing CR |
| 0.9 |
30000? |
42q |
0.98 |
0.22 |
|
| 2.4 |
60000? |
25q |
1.28 |
0.454 |
|
| |
|
|
|
|
|
| 2 |
-- |
-- |
1.2 |
0.403 |
SAE 1890 |
| |
|
|
|
|
|
| 0 |
0 |
49460 |
0.548 |
0 |
Rolls VCE |
| 0.95 |
31000 |
7868 |
0.845 |
0.279 |
|
| 1.3 |
35000 |
12930 |
0.902 |
0.351 |
|
| 2 |
60000 |
8711 |
1.1 |
0.44 |
|
| |
|
|
|
|
|
| 0 |
0 |
------ |
1.39 |
0 |
Rolls Olympus Data |
| 0.95 |
31000 |
----- |
1.025 |
0.23 |
|
| 1.3 |
35000 |
----- |
1.415 |
0.224 |
|
| 2 |
60000 |
---- |
1.195 |
0.405 |
|
| |
|
|
|
|
|
| 0 |
0 |
49460 |
0.551 |
|
Rolls Tandem Fan |
| 0.95 |
31000 |
7868 |
0.816 |
0.288 |
|
| 1.3 |
35000 |
12930 |
0.893 |
0.354 |
|
| 2 |
60000 |
8711 |
1.094 |
0.437 |
|
Overall engine efficiencies at cruise:
| Mach |
eta |
eta_goal |
source |
| 1.0 |
.38 |
.38 |
Douglas CR pg47 |
| 2.0 |
.42 |
.45 |
" |
| 3.2 |
.46 |
.56 |
" |
| 5.0 |
.50 |
.58 |
" |
Some rough additional rules from a Rolls-Royce SNECMA paper:
Nacelle isolated drag = 4.6% T (friction) + 4.4% T (wave)
SLSTH/Weng = 5.28
TOThrust = .37 GTOW (Concorde)