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 |
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For deltawing and ulm airplane |
| SCHEDULE
OF STATIC THRUST |
Engine VICTOR 2 matriculation
V213
Type "C" reduction
ratio 1:276
Double blade pushing propeller
wood made
182x119 GT |
| TESTING
CONDITIONS |
T 2°C -
P 1048 Mb - UR 46%
Locality Torre Maina 17/01/2001
Altitude (S.L.M.) 300 m |
| RPM |
Propeller
Turns |
Kg
of thrust |
| 2200 |
797 |
26 |
| 3125 |
1132 |
69.5 |
| 4075 |
1476 |
91 |
| 4250 |
1540 |
100 |
| 4435 |
1607 |
110 |
| 4700 |
1703 |
120 |
| 5050 |
1730 |
140 |
| 5350 |
1938 |
160 |
| 5800 |
2120 |
180 |
| 5900 |
2137 |
200 |
| 6000 |
2173 |
210 |
| 6200 |
2246 |
225 |
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TECHNICAL DATA
|
|
Displacement
|
cc
|
724
|
|
Bore
|
mm
|
80 x 2
|
|
Stroke
|
mm
|
72 x 2
|
| Compression Ratio |
9,5/1
|
|
Power
|
Hp
|
92
|
|
kW
|
67,53
|
|
RPM
|
6.200
|
| Weight of the engine ready to fly |
Kg 52
|
| Lamellar intake with two Bing
36 carburetors |
| Alluminium cylinders with Nikasil
ceramic coating |
| Exhausts resonance system.
Type "C" reduction |
| Double Ducati electronic ignition
with alternator to recharge battery in fly |
| Electric starter |
| Flying consumption at 5400
RPM, 8 liters/hour |
| Premix two stroke oil gasoline,
2,5% oil by volume to leaded fuel, 3% oil by volume to
unleaded fuel |
|
REDUCTION RATIO AVAIABLE
|
|
1:254 - 1:276 - 1:306 - 1:347 - 1:4
|
|
|
| POWER
AND TORQUE |
 |
| RPM |
Hp |
kW |
Kgm |
| 3000 |
27,6 |
20,31 |
6.58 |
| 3200 |
31,36 |
23,08 |
7,02 |
| 3500 |
37,8 |
27,82 |
7,73 |
| 4000 |
47,2 |
34,74 |
8,45 |
| 4500 |
54,9 |
40,41 |
8,73 |
| 5000 |
68,5 |
50,42 |
9,81 |
| 5500 |
78,65 |
57,89 |
10,24 |
| 6000 |
88,8 |
65,36 |
10,6 |
| 6200 |
91,76 |
67,53 |
10,6 |
| 6500 |
91,65 |
67,45 |
10,01 |
| 6700 |
88,44 |
65,09 |
9,45 |
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