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The "NEXT" is our actual project. It uses foam wing and stab with newly
designed airfoil shown on notes page.
 
 
On bottom of page is table with detailed data giving all dimensions as well as some
numbers helping to trim the model before flying. All is in SI units.
| wing |
|
|
|
wing |
|
|
|
| span |
mm |
1500 |
|
area |
m^2 |
0,45 |
|
| chord root |
mm |
270 |
|
aspect ratio |
|
5,00 |
|
| chord tip in |
mm |
220 |
|
taper |
|
0,74 |
|
| chord tip out |
mm |
220 |
|
C/4 sweepback |
deg |
2,10 |
|
| root flap |
mm |
75 |
|
thickness of airfoil % |
|
0,18 |
|
| tip flap in |
mm |
32,5 |
|
area flaps % |
|
0,18 |
|
| tip flap out |
mm |
37,5 |
|
max. angle flaps |
deg |
29,00 |
|
| tip flap to tip |
mm |
30 |
|
wing loading |
kg/m^2 |
3,56 |
|
| thickness of airfoil root |
mm |
60 |
|
CG % |
|
17,95 |
|
| thickness of airfoil tip |
mm |
50 |
|
max. tension flaps pushrod |
N |
54,49 |
|
|
|
|
|
wing AC offset (level) |
mm |
18,72 |
|
| tail |
|
|
|
wing AC offset (corner) |
mm |
22,41 |
|
| span |
mm |
720 |
|
|
|
|
|
| chord root |
mm |
107 |
|
tail |
|
|
|
| chord tip |
mm |
87 |
|
area |
m^2 |
0,12 |
|
| root flap |
mm |
70 |
|
area tail % wing |
|
0,26 |
|
| tip flap |
mm |
60 |
|
aspect ratio |
|
4,44 |
|
|
|
|
|
C/4 sweepback |
deg |
1,99 |
|
| linkage |
|
|
|
taper |
|
0,83 |
|
| bellcrank max |
Deg |
29 |
|
elevator % tail |
|
0,40 |
|
| bellcrank size |
mm |
100 |
|
max angle tail |
deg |
31,57 |
|
| bellcrank arm |
mm |
27 |
|
max. tension tail pushrod |
N |
7,32 |
|
| horn arm flap |
mm |
27 |
|
|
|
|
|
| horn arm flap/elevator |
mm |
27 |
|
needed line tension |
N |
29,42 |
|
| horn arm elevator |
mm |
25 |
|
centrifugal force |
N |
43,85 |
|
|
|
|
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line tension over head |
N |
28,17 |
|
| lines |
|
|
|
drag lines |
N |
1,95 |
|
| diameter |
mm |
0,38 |
|
lines sweepback (level) |
deg |
2,54 |
|
| lenth |
m |
19,5 |
|
lines sweepback (over head) |
deg |
3,96 |
|
| lap time |
s |
5,5 |
|
lines to flaps (level) |
mm |
158,67 |
|
|
|
|
|
lines to flaps (over head) |
mm |
140,12 |
|
| prop |
|
|
|
lines separation |
mm |
39,75 |
|
| diameter |
" |
12,5 |
|
|
|
|
|
| pitch |
" |
3,5 |
|
Speed |
m/s |
23,99 |
|
| rpm |
1/min |
10500 |
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| weight |
g |
35 |
|
tip weight (sum) |
g |
67,31 |
|
|
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|
|
|
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| fuselage |
|
|
|
engine out (effective) |
deg |
3,68 |
|
| prop-wing |
mm |
270 |
|
arm of engine out |
mm |
22,41 |
|
| flap-tail |
mm |
400 |
|
arm of engine down |
mm |
23,00 |
|
| CG to LE (root) |
mm |
78 |
|
|
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|
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| weight |
g |
1600 |
|
overall engine momentum (level)
(down) |
Nm |
-0,07 |
|
| weight of wing ~ |
g |
400 |
|
overall engine momentum
(corner) (down) |
Nm |
0,01 |
|
| engine out |
Deg |
0 |
|
|
|
|
|
| engine up |
mm |
23 |
|
needed cy wing (corner) |
|
1,69 |
|
| engine down |
Deg |
0 |
|
needed cy tail (corner) |
|
0,35 |
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| fuselage offset right |
mm |
0 |
|
|
|
|
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| landing gears height |
mm |
154 |
|
speed lost in corner |
m/s |
0,62 |
|
| wing mass assymetry |
g |
10 |
|
corner recovery (level) |
deg |
|
|
|
|
|
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corner recovery (level) |
m |
|
|
| corner radius |
m |
3,50 |
|
corner recovery (overhead) |
deg |
0,67 |
|
|
|
|
|
corner recovery (overhead) |
m |
0,24 |
|
| ruder height |
mm |
200 |
|
lines retire (level) |
m |
|
|
| ruder length |
mm |
200 |
|
lines retire (overhead) |
m |
0,04 |
|
| ruder flap length (average) |
mm |
20 |
|
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|
|
|
|
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angle of attack wing before
corner |
deg |
16,83 |
|
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|
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angle of attack wing in corner |
deg |
6,59 |
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|
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reserve of wing cy in corner |
|
0,18 |
|
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CG front neutral point |
mm |
149,14 |
|
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|
|
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momentum CG to neutral point |
mNm |
84,51 |
|
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momentum to mass |
|
5,28 |
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static reserve of stability |
% |
24,02 |
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Rabe ruder deflection +/- |
deg |
9,78 |
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