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Skycar Performance Specifications (Projected)  Dec 2000  
       
these are the latest released specifications as of 2/01

 MODEL

 M400 SKYCAR

(PROTOTYPE VERSION)

 M400 SKYCAR

(PRODUCTION VERSION)

 Passengers

 4

 4

 Maximum speed @ S.L. 
        (no boost)  
 Maximum cruise speed
     (75% maximum range)

397 mph  

245 mph @ sea level
285 mph @ 10,000 ft.
335 mph @ 20,000 ft.
352 mph @ 25,000 ft.

368 mph  
 
228 mph @ sea level
265 mph @ 10,000 ft.
312 mph @ 20,000 ft.
326 mph @ 25,000 ft.

 Rate of climb @ power avail.

 (Limit M400 Prototype to 
     790 hp  @ sea level)

7,800 fpm @ sea level
7,200 fpm @ 10,000 ft.
3,900 fpm @ 20,000 ft.
1,450 fpm @ 30,000 ft.

7,050 fpm @ sea level
4,300 fpm @ 10,000 ft.
2,400 fpm @ 20,000 ft.
  
850 fpm @ 30,000 ft.

 Maximum range (Max. AUW)

      (15-minute reserve)

         924 miles @  
165 mph @ sea level
190 mph @ 10,000 ft.
225 mph @ 20,000 ft.
270 mph @ 30,000 ft.

        920 miles @  
145 mph @ sea level
170 mph @ 10,000 ft.
200 mph @ 20,000 ft.
240 mph @ 30,000 ft.

  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.)

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

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)

  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

 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

 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

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).