VTOL Vantage

CONTROL

IOPT= 1 3 4

PDES= 0

END

DESLIM

ABMIN= 10.00000000000000

AFLIM= 50.00000000000000 150.0000000000000

CLDES= 0.0000000000000000

DMAX= 110.0000000000000

END

DESVAR

ADRAG= 2.000000000000000

AFDES= 56.58790842999272

ALTCRS= 0.0000000000000000

KS= 2.500000000000000

DIAM= 91.00000000000000

OSWALD= 0.8250000000000000

PITCH= 100.0000000000000

RPMCRS= 2500.000000000000

SPAN= 28.75000000000000

VCRS= 230.0000000000000

WTGRSS= 660.0000000000000

END

TABLES

STA= 0.2000000029802322 0.3000000119209290

0.4000000059604645 0.5000000000000000

0.6000000238418579 0.6999999880790710

0.8000000119209290 0.8999999761581421

1.000000000000000

CHORD= 4.430801863459890 4.363707109808505

4.322940795115224 4.266037316403554

4.120807294997606 3.844784317964609

3.465146873382407 2.908005686824693

2.251496228535101

TCTAB= 0.4063999950885773 0.2937000095844269

0.2435999959707260 0.2006999999284744

0.1684000045061111 0.1439999938011169

0.1354999989271164 0.1150999963283539

0.9019999951124191E-01

END

END

CONTROL

IOPT=

;

PDES=

END

DESLIM

ABMIN=

AFLIM=

;

CLDES=

DMAX=

END

DESVAR

ADRAG=

1.35

AFDES=

40

ALTCRS=

KS=

10

DIAM=

OSWALD=

PITCH=

110

RPMCRS=

SPAN=

VCRS=

WTGRSS=

END

TABLES

END

VTOL Vantage

@ 02/12/08 21:34:27.00

>>>> OPTIMIZED DESIGN:

VARIABLE INITIALLY OPTIMIZED LOWER LIMIT UPPER LIMIT

AFDES 50.0000 51.8009 50.0000 150.000

PITCH 110.000 104.223 55.0000 220.000

RPM 2500.00 1965.52 1800.00 2700.00

PROPELLER DESIGN CRUISE PERFORMANCE

NUMBER OF BLADES = 2 VELOCITY, MPH = 230.000

BLADE ACTIVITY FACTOR= 51.8009 ALTITUDE, FEET = 0.00

DIAMETER, INCHES = 91.0000 DENSITY, SLUGS = 0.237800E-02

GEOMETRIC PITCH, IN = 104.223 THRUST, POUNDS = 208.650

EFFECTIVE PITCH, IN = 123.570 DRAG, POUNDS = 208.650

ABSOLUTE PITCH, IN = 129.649 THRUST HP = 127.972

SHAFT HP = 145.043

ALPHA @ 0LL DEG @75%R= 1.20438 HP AVAILABLE = 145.043

DESIGN LIFT COEF, CL = 0.2013 PROPELLER RPM = 1965.52

THRUST COEF, CT = 0.0247 ENGINE RPM = 1965.52

POWER COEF, CP = 0.0381 REDUCT FACTOR = 1.00000

ADVANCE RATIO, J = 1.35792 SFC, LB/HP/HR = 0.580019

MILES/GALLON = 16.4037

EFFICIENCY, ETA = 0.882305 FUEL FLOW, PPH = 84.1274

ETA COMPRESS CORRECT.= 0.00% FUEL FLOW, GPH = 14.0212

ETA PROFILE DRAG CORR= 1.21% SOUND SPEED,FPS= 1116.41

ETA DIAMETER CORRECT.= 0.00% TIP SPEED, FPS = 850.218

ADRAG, SQ FT = 1.35000 TIP MACH NUMBER= 0.761567

CONSTRAINT VALUES MEASURE THE SUCCESS OF THE OPTIMIZATION.

EQUALITY CONSTRAINTS ARE SATISFIED WHEN = 0

INEQUALITY CONSTRAINTS ARE SATISFIED WHEN >= 0

TYPE: EQUALITY = 0, UPPER BOUND = 1, LOWER BOUND = -1

SYSTEM CONSTRAINT VALUES:

NAME TYPE ACTIVE INACTIVE REQUIREMENT

CRUISE SHP=HPA 0 -0.1292E-07 SATISFIED

THRUST=DRAG 0 -0.1602E-07 SATISFIED

PAYOFF=-2.30000 (-VCRS) TRIAL RUNS = 53

GENERAL NOMENCLATURE

AFDES Activity factor per blade. The higher the activity factor,

the more power a blade can absorb (or is required). For a

given diameter, activity factor increases with blade width.

ALPHA Blade angle-of-attack at the 75% radius, degrees. The angle

the incoming air flow makes with the airfoil zero-lift-line.

ANGLE Blade pitch angle at 75% tip radius station measured

with respect to the plane of rotation, degrees.

CL Blade lift coefficient. Design lift coefficient for cruise.

CP Power coefficient: A non dimensional ratio relating power

required to air density, propeller speed squared and

propeller diameter raised to the fifth power. Power

required is proportional to the fifth power of diameter

for other factors being equal.

GENERAL NOMENCLATURE

CT Thrust coefficient: A non dimensional ratio relating thrust

produced to air density, propeller speed squared and

propeller diameter raised to the fourth power. Thrust

produced is proportional to the fourth power of diameter

for other factors being equal.

CS SPEED_POWER coefficient, J/CP^(1/5). A design parameter used

in determining maximum efficiency for cruise propellers.

DIAM Propeller diameter, inches

DRAG Aircraft drag, pounds

ETA Propeller efficiency: ETA=CT*J/CP

A measure of how much power is delivered to the air stream

by the propeller relative to power delivered by the engine.

This value includes compressibility, profile drag and

relative diameter corrections.

GENERAL NOMENCLATURE

ETA COMPRESS CORRECT: A factor indicating the percentage propeller

efficiency is reduced due to sonic compressibility effects

at the blade tip. Zero indicates no compressibility losses.

The optimizer tries to design on balance to minimum loss.

ETA PROFILE DRAG CORR: An efficiency correction due to blade width

or total activity factor and represents the induced losses.

ETA DIAMETER CORRECT: Corrects for the relative influence of body

and engine nacelle size to propeller diameter. Assuming that

the reference point is accounted for in the effective pitch

and ADRAG calibration, this correction is the increase or

decrease in efficiency from the calibrated reference point.

FFGPH Fuel flow in gallons per hour

FFPPH Fuel flow in pounds per hour

HPA Maximum Horsepower Available from the engine at any

given engine rpm.

GENERAL NOMENCLATURE

J Advance ratio J=(V*88)/(RPM*DIAMETER) Where: V=mph,

DIAMETER=ft. In flight the propeller advances a distance

of J times the DIAMETER per revolution.

MPG Aircraft miles per gallon of fuel

NB Number of blades

PITCH Pitch of chord line at the 75% radius station, inches.

The geometric or theoretical advance of the propeller

per revolution.

RHO Atmospheric density, slugs

SFC Specific fuel consumption, lb/hp/hr

SHP Shaft horsepower required at the propeller shaft before

efficiency losses.

THRUST Propeller thrust, pounds

GENERAL NOMENCLATURE

THP Net Thrust Horsepower delivered to the atmosphere by the

propeller after efficiency losses and required for flight,

(THP=SHP*ETA).

TPMACH Tip Mach number

V Aircraft velocity, miles/hour

VS Speed of sound, feet/second

VT Tip speed, feet/second

NRUN Number of trial designs run

PAYOFF Objective or merit function. A quantitative measure of

the design goal such as maximum velocity or climb rate.

PROP OPTIMIZER (tm)

Copyright 1994 Donald R Bates - All Rights Reserved

BATES ENGINEERING, 2742 Swansboro Road, Placerville, CA 95667

Phone/FAX 916-622-1886

Copy Date 12/11/94