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06-18-2005, 05:28 AM
I need as much actual data as possible to verify a calculation routine (thanks):

DATA********************************************** **
GYRO @ 2 X 8H12 BLADES ( 30 ft.) OF c= 8.5 INCHES @ 4 DEGREES
GROSS WEIGHT = 1370 lbs. EQUIV. FRONT FLAT AREA = 10.5 ft^2.
GYRO SPEED = 75 mph. ( 109.95 ft/s.) @ 500 ft. ASL.
ENGINE POWER = 130 hp.ASL ( 128.375 @ 500 ft.) PROP. 68 '' @ 2620 rpm.
************************************************** ******

the routine will figure out the numbers:

************************************************** *********************
>>>>> RAF2000 STANDARD CONFIGURATION...
GYRO @ 2 X 8H12 BLADES ( 30 ft.) OF c= 8.5 INCHES @ 4 DEGREES
GROSS WEIGHT = 1370 lbs. EQUIV. FRONT FLAT AREA = 10.5 ft^2.
GYRO SPEED = 75 mph. ( 109.95 ft/s.) @ 500 ft. ASL.
ENGINE POWER = 130 hp.ASL ( 128.375 @ 500 ft.) PROP. 68 '' @ 2620 rpm.
ROTOR SIGMA = 0.030 (SOLIDITY RATIO: best ~.035 @ .040)
************************************************** *********************
RPM ROTOR= 374.9 rpm.
TIP BLADE SPEED = 588.9 ft./s. ( 326.6 mph. MIN. TO 476.6 mph. MAX.)
NU (GYRO SPEED/TIP SPEED)= 0.19 (best~ 0.3)
ROTOR DRAG = 178.5 lbs. FRAME DRAG = 148.8 lbs. TOTAL DRAG = 327.3 lbs.
ROTOR L/D= 7.7 GLOBAL L/D= 4.2
NEEDED POWER= 65.4 hp.
STATIC THRUST = 505.9 lbs. PROP. TIP @ 777.4 ft./sec. (best < 800)
AVAILABLE POWER = 76.6 hp. AVAILABLE THRUST = 382.9 lbs.
************************************************** *********************
USES 85.5 % OF AVAILABLE THRUST
PROP EFFICIENCY = 58.9 %
RATE OF CLIMB = 233.0 ft./min. @ 100%hp @ 75.0 mph. @ 500.0 feet
VERTICAL DESCENT W/O ENGINE = 1859.4 ft./min. ROTOR @ 358.5 rpm.
************************************************** *********************

06-20-2005, 08:38 AM
...i give you an other example...correct me...

************************************************** *********************
06-20-2005 11:27:03
************************************************** *********************
>>>>> MAGNI M16 TANDEM TRAINER
GYRO @ 2 8H12 BLADES ( 27 ft.) OF c= 8.7 INCHES @ 4 DEGREES
GROSS WEIGHT = 1200 lbs. EQUIV. FRONT FLAT AREA = 8.87 ft^2.
GYRO SPEED = 65 mph. ( 95.29 ft/s.) @ 500 ft. ASL.
ENGINE POWER = 115 hp.ASL ( 113.5625 @ 500 ft.) PROP. 67 '' @ 2620 rpm.
ROTOR SIGMA = 0.034 (SOLIDITY RATIO: best ~.035 @ .040)
************************************************** *********************
RPM ROTOR= 399.9 rpm.
TIP BLADE SPEED = 565.3 ft./s. ( 320.5 mph. MIN. TO 450.5 mph. MAX.)
NU (GYRO SPEED/TIP SPEED)= 0.17 (best~ 0.3)
ROTOR DRAG = 185.3 lbs. FRAME DRAG = 94.4 lbs. TOTAL DRAG = 279.7 lbs.
ROTOR L/D= 6.5 GLOBAL L/D= 4.3
NEEDED POWER= 48.5 hp.
STATIC THRUST = 468.9 lbs. PROP. TIP @ 765.9 ft./sec. (best < 800)
AVAILABLE POWER = 63.2 hp. AVAILABLE THRUST = 364.8 lbs.
************************************************** *********************
USES 76.7 % OF AVAILABLE THRUST
PROP EFFICIENCY = 55.0 %
RATE OF CLIMB = 342.9 ft./min. @ 100%hp @ 65.0 mph. @ 500.0 feet
VERTICAL DESCENT W/O ENGINE = 1917.3 ft./min. ROTOR @ 388.4 rpm.
************************************************** *********************
06-20-2005 11:29:58
************************************************** *********************
>>>>> MAGNI M16 WITH 1 PILOT
GYRO @ 2 8H12 BLADES ( 27 ft.) OF c= 8.7 INCHES @ 4 DEGREES
GROSS WEIGHT = 900 lbs. EQUIV. FRONT FLAT AREA = 8.87 ft^2.
GYRO SPEED = 65 mph. ( 95.29 ft/s.) @ 500 ft. ASL.
ENGINE POWER = 115 hp.ASL ( 113.5625 @ 500 ft.) PROP. 67 '' @ 2620 rpm.
ROTOR SIGMA = 0.034 (SOLIDITY RATIO: best ~.035 @ .040)
************************************************** *********************
RPM ROTOR= 354.5 rpm.
TIP BLADE SPEED = 501.1 ft./s. ( 276.7 mph. MIN. TO 406.7 mph. MAX.)
NU (GYRO SPEED/TIP SPEED)= 0.19 (best~ 0.3)
ROTOR DRAG = 118.2 lbs. FRAME DRAG = 94.4 lbs. TOTAL DRAG = 212.6 lbs.
ROTOR L/D= 7.6 GLOBAL L/D= 4.2
NEEDED POWER= 36.8 hp.
STATIC THRUST = 468.9 lbs. PROP. TIP @ 765.9 ft./sec. (best < 800)
AVAILABLE POWER = 63.2 hp. AVAILABLE THRUST = 364.8 lbs.
************************************************** *********************
USES 58.3 % OF AVAILABLE THRUST
PROP EFFICIENCY = 55.0 %
RATE OF CLIMB = 840.2 ft./min. @ 100%hp @ 65.0 mph. @ 500.0 feet
VERTICAL DESCENT W/O ENGINE = 1660.4 ft./min. ROTOR @ 336.4 rpm.
************************************************** *********************

pwendell
06-20-2005, 09:55 AM
The RRPM is WAY high for the RAF. In the AAI mod RAFs I flew, we would show around 315-20 dual with Sportcopter blades.

06-20-2005, 10:26 AM
First, the calculation are made for an aerodynamic pitch of 4 degrees. If the pitch is higher, all other things being equal, the RRPM is less and the efficiency is better. 4 degrees is OK not to have problem during hand proping and/or during the accelerating phase (flapping) before taking off, or in flight at high speed; knowing that a less RRPM means a higher tower too, or heavy tips. It seems that for recreational purpose, 4 degrees is an optimum. Martin Hollman recommands the highest pitch for efficiency but without having problem!!! :)

cf: GYROPLANE PERFORMANCE CALCULATIONS AND TRENDS, Sport aviation may 1975, Martin Hollman and/or his MODERN GYROPLANE DESIGN...

pwendell
06-20-2005, 01:16 PM
I don't know. It's not my aircraft.

MikeyT
07-31-2005, 03:28 PM
Hi

I'm new to this forum so please excuse if this is a dumb question.

What routine did you use to calculate static thrust? I would really love to get access to that.

can you send it to me or tell me where to get it?