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More adjustments for addition power:

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Corrected empty + pilot aircraft mass to 7190.
Upped "cruise speed" to maximum operational speed of 380 knots.
Reduced prop pitch at cruise to 0.8 (3000 rpm is only for takeoff).
Changed camber to 0.01 (found reference that said 1%)
Decreased tail surface effectiveness slightly just to get better numbers.
Changed turbo-mult to 2.5 and wastegate-mp to 30
This commit is contained in:
jimw 2003-05-07 02:01:42 +00:00
parent c0559d20a1
commit 97c2e8f59a
1 changed files with 7 additions and 7 deletions
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14
Aircraft-yasim/p51d.xml
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@ -29,7 +29,7 @@ The reference datum for measurements is the nose.
-->
<!-- Weight of everything but fuel (7010 empty) -->
<airplane mass="7390">
<airplane mass="7190">
<!-- Approach configuration -->
<approach speed="87" aoa="13">
@ -42,10 +42,10 @@ The reference datum for measurements is the nose.
<!-- Cruise configuration -->
<!-- 350 mph, 304 knots -->
<cruise speed="304" alt="25000">
<cruise speed="380" alt="25000">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.00"/>
<control-setting axis="/controls/engines/engine[0]/mixture" value="1.00"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="1.0"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.8"/>
<control-setting axis="/controls/engines/engine[0]/boost" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="0"/>
@ -62,7 +62,7 @@ stall aoa not available
flap drag not available
-->
<wing x="-3.96" y="0.49" z="-0.67" taper="0.466" incidence="-1"
length="5.16" chord="2.845" sweep="3.5" dihedral="5" camber=".1">
length="5.16" chord="2.845" sweep="3.5" dihedral="5" camber="0.01">
<stall aoa="14" width="4" peak="1.5"/>
<flap0 start="0.024" end="0.543" lift="1.2" drag="1.4"/>
<flap1 start="0.543" end="0.97" lift="1.2" drag="1.4"/>
@ -73,7 +73,7 @@ flap drag not available
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
</wing>
<hstab x="-8.62" y="0.18" z="0.35" taper="0.639" effectiveness="4.0"
<hstab x="-8.62" y="0.18" z="0.35" taper="0.639" effectiveness="3.5"
length="1.834" chord="1.256" sweep="0" incidence="2">
<stall aoa="15" width="4" peak="1.5"/>
<flap0 start="0.0" end="1.8" lift="1.65" drag="1.2"/>
@ -83,7 +83,7 @@ flap drag not available
</hstab>
<!-- rudder has to be able to counteract aileron drag -->
<vstab x="-9.30" y="0" z="-0.37" taper="0.432" effectiveness="4.0"
<vstab x="-9.30" y="0" z="-0.37" taper="0.432" effectiveness="3.5"
length="1.971" chord="2.65" sweep="25">
<stall aoa="15" width="4" peak="1.5"/>
<flap0 start="0" end="1" lift="1.3" drag="1.2"/>
@ -97,7 +97,7 @@ flap drag not available
radius="1.75"
mass="1690" moment="110"
eng-power="1490" eng-rpm="2300"
turbo-mul="2.0" wastegate-mp="47"
turbo-mul="2.5" wastegate-mp="30"
cruise-alt="25000" cruise-power="1350"
cruise-speed="304" cruise-rpm="2700"
min-rpm="800" max-rpm="3000" >