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Skycar
Performance Specifications (Projected) Dec
2000
these are
the latest released specifications as of 2/01
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MODEL
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M400
SKYCAR
(PROTOTYPE
VERSION)
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M400
SKYCAR
(PRODUCTION
VERSION)
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Passengers
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4
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4
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Maximum speed @ S.L.
(no boost)
Maximum cruise
speed
(75% maximum range)
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397 mph
245 mph @ sea level
285 mph @ 10,000 ft.
335 mph @ 20,000 ft.
352 mph @ 25,000 ft.
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368 mph
228 mph @ sea level
265 mph @ 10,000 ft.
312 mph @ 20,000 ft.
326 mph @ 25,000 ft.
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Rate of climb @ power
avail.
(Limit M400 Prototype to
790
hp @ sea level)
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7,800 fpm @ sea
level
7,200 fpm @ 10,000 ft.
3,900 fpm @ 20,000 ft.
1,450 fpm @ 30,000 ft.
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7,050 fpm @ sea
level
4,300 fpm @ 10,000 ft.
2,400 fpm @ 20,000 ft.
850 fpm @ 30,000 ft.
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Maximum range (Max. AUW)
(15-minute reserve)
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924 miles @
165 mph @ sea level
190 mph @ 10,000 ft.
225 mph @ 20,000 ft.
270 mph @ 30,000 ft.
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920 miles @
145 mph @ sea level
170 mph @ 10,000 ft.
200 mph @ 20,000 ft.
240 mph @ 30,000 ft.
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Maximum mileage
Fuel capacity (useable)
Maximum payload (inc. fuel)
Hover ceiling (OGE)
Operational ceiling
Gross weight
Power required (hover @ S.L.)
Power available (flight @ S.L.)
Power (installed at S.L.)
Power (maximum at S.L.)
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16 mpg
60 gallons
1,000 lbs.
10,000 ft.
30,000 ft.
2,400 lbs.
655 hp
1,050 hp
1,050 hp
1,050 hp
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26 mpg
35 gallons
875 lbs.
10,000 ft. (boosted)
30,000 ft.
2,400 lbs.
680 hp
660 hp
770 hp
1,400 hp (boosted)
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Number of ducted
fans
Disc loading (uses exit area)
Dimensions (folded)
Span (unfolded)
Aspect ratio
Span efficiency factor *
Profile drag coefficient~CDw*
Wetted area (exterior)
Equivalent flat plate drag area
Effective wing area*
Maximum lift to drag ratio
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4
133 lbs./ft.²
18.5 ft. L; 10 ft. W; 6.5 ft. H
14 ft.
3
0.83
.0045
420 ft.²
1.9 ft. ²
80 ft.²
9.1
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3
146 lbs./ft.²
18.5 ft. L; 8.5 ft. W; 6.5 ft. H
18 ft.
6
0.87
.004
375 ft.²
1.5 ft.²
78 ft.²
14.6
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The Skycar’s projected performance is based on the following design and operating conditions:
1-Specific fuel consumption is .4 lbs./hp hr. This S.F.C. requires the engine to use stratified charge.
2-Power at altitude is given by: Power = (1.132σ - .132) x installed
horsepower. (σ = air density ratio)
3-Pitch control of all fans is required to maintain good
propulsive efficiency during both hover and cruise
4-Duct propulsive efficiency is assumed to be 80% based on thrust tests to date.
5-The high rate of climb and high speed cruise capability of the
Skycar will require cabin pressurization to be effectively used.
*These design data are determined from scale model tests in a wind-tunnel. Full-scale tests are expected to alter these numbers
somewhat; however, the Skycar’s projected speeds are consistent
with other aircraft having similar power/wetted area ratios (P51
Mustang, TBM 700, XV-15, Lancair IV).
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