Item 0915
DESIGN: UniCopter ~
Trim, Stability & Control - Trim - Horizontal Stabilizer
Note:
The Horizontal Stabilizer may not be necessary. See UniCopter ~ Trim, Stability & Control - Stability - Angle of Attack Stability - Decalage.
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Configuration Parameters: |
Symbol: |
Value: |
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Incidence of the chord line |
iH |
8.0 |
deg. |
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Slope of Lift Chord (aH) |
aH |
0.06 |
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Angle of zero lift (alphaLOH) |
α LOH |
0.0 |
deg. |
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Span Efficiency Factor |
δ iH |
1.0 |
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Zero Lift Drag Coefficient |
CD0H |
0.006 |
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Forces on Horizontal Stabilizer:
For calculation on the area of the horizontal stabilizer [
AH] see: Dimension & Area - View - Plan (X-Y plane)α
H = Θ + iH + γcC
LH = a H * (α H - αL0H)L
H = AH * CLHD
H = AH * [(C2LH / (π * AR H )) * (1 + δi H) + CD0 H ]The dynamic pressure ratio [
(qH /q) * q] will be 1 since the horizontal stabilizer is not in the effects of the rotors or fuselage. It has therefor been removed from the above equations.|
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XH = |
LH * sin[Θ - γc] - DH * cos[Θ - γc] |
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YH = |
-LH * cos[Θ - γc] - DH * sin[Θ - γc] |
The downwash (upwash) angles of [
εPH + εSH + εFH] have been removed from the above equations since they will be zero in all conditions. A possible exception is autorotation but even in this condition, the outer portion of the rotor disks is driving air downward and away from the tail.
Notes:
Consider 1/ sweeping the HS further aft (considering Wortmann FX 74 CL5-140, if it can operate at high forward speeds)
0920.html, 2/ increasing the surface area slightly, 3/ providing small VS at the tips of the HS and 4/ decreasing the angle of incidence slightly.
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Last Revised: January 25, 2007