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The "TINY" is another our actual project. It uses paper sheeted foam wing
with newly designed airfoil shown on notes page.
550g heavy model with .15 engine easily flies full F2B pattern on 17m lines. I was
surprised with its flying ability. I can say it is much easier to fly full pattern than
with full size F2B model (unfortunately only in calm condition). I recommend it to all
those who want to learn F2B pattern.
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.
Here is example of 2 models differing in look only. Both use paper/foam wing and 4mm
thin balsa flaps, stab and elevator. First one uses old cross scavened Os Max .15 with 9x4
prop and clunk tank - good choice for beginners.
Second, nice looking is the same layout, just better finished.
Here are some details:
| wing |
|
|
|
wing |
|
|
|
| span |
mm |
1000 |
|
area |
m^2 |
0,23 |
|
| chord root |
mm |
220 |
|
aspect ratio |
|
4,27 |
|
| chord tip in |
mm |
160 |
|
taper |
|
0,67 |
|
| chord tip out |
mm |
160 |
|
C/4 sweepback |
deg |
4,25 |
|
| root flap |
mm |
60 |
|
thickness of airfoil % |
|
0,19 |
|
| tip flap in |
mm |
27 |
|
area flaps % |
|
0,19 |
|
| tip flap out |
mm |
30 |
|
max. angle flaps |
deg |
27,00 |
|
| tip flap to tip |
mm |
0 |
|
wing loading |
kg/m^2 |
2,99 |
|
| thickness of airfoil root |
mm |
50 |
|
CG % |
|
15,58 |
|
| thickness of airfoil tip |
mm |
40 |
|
max. tension flaps pushrod |
N |
33,69 |
|
|
|
|
|
wing AC offset (level) |
mm |
9,29 |
|
| tail |
|
|
|
wing AC offset (corner) |
mm |
10,86 |
|
| span |
mm |
460 |
|
|
|
|
|
| chord root |
mm |
80 |
|
tail |
|
|
|
| chord tip |
mm |
60 |
|
area |
m^2 |
0,06 |
|
| root flap |
mm |
60 |
|
area tail % wing |
|
0,25 |
|
| tip flap |
mm |
50 |
|
aspect ratio |
|
3,68 |
|
|
|
|
|
C/4 sweepback |
deg |
3,11 |
|
| linkage |
|
|
|
taper |
|
0,79 |
|
| bellcrank max |
Deg |
27 |
|
elevator % tail |
|
0,44 |
|
| bellcrank size |
mm |
100 |
|
max angle tail |
deg |
29,96 |
|
| bellcrank arm |
mm |
20 |
|
max. tension tail pushrod |
N |
5,37 |
|
| horn arm flap |
mm |
20 |
|
|
|
|
|
| horn arm flap/elevator |
mm |
22 |
|
needed line tension |
N |
13,48 |
|
| horn arm elevator |
mm |
20 |
|
centrifugal force |
N |
20,45 |
|
|
|
|
|
line tension over head |
N |
13,59 |
|
| lines |
|
|
|
drag lines |
N |
1,27 |
|
| diameter |
mm |
0,3 |
|
lines sweepback (level) |
deg |
3,54 |
|
| lenth |
m |
17 |
|
lines sweepback (over head) |
deg |
5,32 |
|
| lap time |
s |
5 |
|
lines to flaps (level) |
mm |
124,04 |
|
|
|
|
|
lines to flaps (over head) |
mm |
108,41 |
|
| prop |
|
|
|
|
|
|
|
| diameter |
" |
9 |
|
|
|
|
|
| pitch |
" |
4 |
|
Speed |
m/s |
23,25 |
|
| rpm |
1/min |
11000 |
|
|
|
|
|
| weight |
g |
18 |
|
tip weight (sum) |
g |
19,70 |
|
|
|
|
|
|
|
|
|
| fuselage |
|
|
|
engine out (effective) |
deg |
3,93 |
|
| prop-wing |
mm |
170 |
|
arm of engine out |
mm |
17,09 |
|
| flap-tail |
mm |
300 |
|
arm of engine down |
mm |
23,49 |
|
| CG to LE (root) |
mm |
65 |
|
|
|
|
|
| weight |
g |
600 |
|
overall engine momentum (level)
(down) |
Nm |
-0,01 |
|
| weight of wing ~ |
g |
200 |
|
overall engine momentum
(corner) (down) |
Nm |
0,05 |
|
| engine out |
Deg |
2,5 |
|
|
|
|
|
| engine up |
mm |
10 |
|
needed cy wing (corner) |
|
1,50 |
|
| engine down |
Deg |
1,5 |
|
needed cy tail (corner) |
|
0,43 |
|
| fuselage offset right |
mm |
5 |
|
|
|
|
|
| landing gears height |
mm |
120 |
|
speed lost in corner |
m/s |
0,86 |
|
|
|
|
|
corner recovery (level) |
deg |
|
|
|
|
|
|
corner recovery (level) |
m |
|
|
| corner radius |
m |
3 |
|
corner recovery (overhead) |
deg |
0,00 |
|
|
|
|
|
corner recovery (overhead) |
m |
0,00 |
|
|
|
|
|
lines retire (level) |
m |
|
|
|
|
|
|
lines retire (overhead) |
m |
0,00 |
|
|
|
|
|
|
|
|
|
|
|
|
|
angle of attack wing before
corner |
deg |
15,97 |
|
|
|
|
|
angle of attack wing in corner |
deg |
6,67 |
|
|
|
|
|
reserve of wing cy in corner |
|
0,18 |
|
|
|
|
|
|
|
|
|
|
|
|
|
CG front neutral point |
mm |
115,70 |
|
|
|
|
|
momentum CG to neutral point |
mNm |
33,76 |
|
|
|
|
|
momentum to mass |
|
5,63 |
|
|
|
|
|
|
|
|
|
|
|
|
|
static reserve of stability |
% |
24,43 |
|
|
|
|
|
|
|
|
|
|
|
|
|
elevator roll (in) |
deg |
3,45 |
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