3 BLADE PROP FOR COZY-4 Lyc 0-360 SAMPLE DESIGN
CONTROL
NPAYOFF=2
AIRFOIL=2 @ 1 is clark Y, 2 is RAF 6
IOPT=1,2,3,4,5,6,7
BLDOP=1
pdes=1
END
DESLIM
AFLIM=60,180
abmin=1.55 @ cldes=.4
DMAX= 68
RCLM=1
END
DESVAR
REDFAC=1.0
DIAM=68 PITCH=72
NB=3
RPMCRS=2600 ALTCRS=2000
DREF=70
WT0=1200
WPAYLD=700
SPAN=28
OSWALD=.851
SFCLM=1
sfcrs=.1
pctpwr=100
VCRS=210
RPMCLM=2500
VCLM=110
ALTCLM=2000
KS=1.00
ADRAG=1.9
END
TABLES
STA= .2, .3, .4, .5, .6, .7, .8, .9, 1.
CHORD=5.717 5.638 5.50 5.423 5.252 4.827 4.380 3.624 2.851
TCTAB=.4064 .2937 .2436 .2007 .1684 .1440 .1355 .1151 .0902
RPMTAB=1800 2250 2700
HPTAB= 132 164 180
SFCTAB= .6 .55 .52
END
EOF
3 BLADE PROP FOR COZY-4 Lyc 0-360 SAMPLE DESIGN
@ 12/08/97 02:21:51.85
>>>> OPTIMIZED DESIGN:
VARIABLE INITIALLY OPTIMIZED LOWER LIMIT UPPER LIMIT
AFDES 94.0139 69.6166 60.0000 180.000
DIAM 68.0000 68.0000 13.6000 68.0000
PITCH 72.0000 72.4139 36.0000 144.000
RPMCRS 2600.00 2700.00 1800.00 2700.00
VCRS 210.000 217.693 157.500 262.500
RPMCLM 2500.00 2197.02 1800.00 2700.00
VCLM 110.000 124.232 82.5000 137.500
PROPELLER DESIGN CRUISE PERFORMANCE, ALT= 2000.00 FT
NUMBER OF BLADES = 3 VELOCITY, MPH = 217.69
BLADE ACTIVITY FACTOR= 69.62 THRUST, POUNDS = 239.20
DIAMETER, INCHES = 68.00 DRAG, POUNDS = 239.20
GEOMETRIC PITCH, IN = 72.41 EFFECTIVE PITCH, IN = 85.14
ABSOLUTE PITCH, IN = 90.86 THRUST HP = 138.86
BLADE ANGLE DEG @75%R= 29.56 SHAFT HP = 167.73
ALPHA @ 0LL DEG @75%R= 1.57 HP AVAILABLE = 167.73
DESIGN LIFT COEF, CL = 0.2420 PROPELLER RPM = 2700.00
THRUST COEF, CT = 0.0511 ENGINE RPM = 2700.00
POWER COEF, CP = 0.0773 REDUCT FACTOR = 1.00
ADVANCE RATIO, J = 1.2521 PARASITE DRAG,LB = 217.04
EFFICIENCY, ETA = 0.8278 INDUCED DRAG, LB = 15.08
ETA COMPRESS CORRECT.= 0.00% SLIPSTREAM DRAG = 7.08
ETA PROFILE DRAG CORR= 0.28% SFC, LB/HP/HR = 0.52
ETA DIAMETER CORRECT.= -0.38% MILES/GALLON = 14.98
FUEL FLOW, GPH = 14.54
SLIPSTREAM COEF, KS = 1.0000 SOUND SPEED,FPS = 1108.75
ADRAG, SQ FT = 1.900 TIP SPEED, FPS = 862.39
GROSS WEIGHT, LB = 1900.0 TIP MACH NUMBER = 0.78
WPAYLD, LB = 700.0 CAFE CHALLENGE = 834897.
CLIMB PERFORMANCE AT V= 124.23 MPH, ALTITUDE= 2000.00
NUMBER OF BLADES = 3 CLIMB RATE, FPM = 1300.46
BLADE ACTIVITY FACTOR= 69.62 THRUST, POUNDS = 353.45
DIAMETER, INCHES = 68.00 DRAG, POUNDS = 127.44
EFFECTIVE PITCH, IN = 59.71 THRUST HP = 117.09
BLADE ALPHA DEG @75%R= 9.12 SHAFT HP = 150.04
BLADE LIFT COEF, CL = 0.9899 HP AVAILABLE = 150.04
PROPELLER RPM = 2197.02
THRUST COEF, CT = 0.1141 ENGINE RPM = 2197.02
POWER COEF, CP = 0.1284 PARASITE DRAG,LB = 70.68
ADVANCE RATIO, J = 0.8781 INDUCED DRAG, LB = 46.30
EFFICIENCY, ETA = 0.7804 SLIPSTREAM DRAG = 10.46
ETA COMPRESS CORRECT.= 0.00% GROSS WEIGHT, LB = 1900.00
ETA PROFILE DRAG CORR= 0.06% SOUND SPEED,FPS = 1108.75
ETA DIAMETER CORRECT.= -0.38% TIP SPEED, FPS = 676.85
ADRAG, SQ FT = 1.900 TIP MACH NUMBER = 0.61
PROPELLER BLADE SHAPE
_____STATION_____ CHORD ___THICKNESS___ CHORD ANGLE ___LOCAL___
R/R(TIP) INCHES INCHES RATIO INCHES DEGREES MACH REYN
0.2000 6.80 4.23 0.4064 1.72 49.66 0.156 3.7E+05
0.3000 10.20 4.17 0.2937 1.23 43.57 0.233 5.5E+05
0.4000 13.60 4.07 0.2436 0.99 37.32 0.311 7.1E+05
0.5000 17.00 4.02 0.2007 0.81 32.59 0.389 8.8E+05
0.6000 20.40 3.89 0.1684 0.65 28.84 0.467 1.0E+06
0.7000 23.80 3.57 0.1440 0.51 25.82 0.544 1.1E+06
0.8000 27.20 3.24 0.1355 0.44 22.96 0.622 1.1E+06
0.9000 30.60 2.68 0.1151 0.31 21.13 0.700 1.1E+06
1.0000 34.00 2.11 0.0902 0.19 19.91 0.778 9.2E+05
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 6.800 BLADE ANGLE= 49.661 DEG
X YU YL
0.000 0.172 0.172
0.106 0.705 0.013
0.212 1.015 0.000
0.423 1.359 0.000
0.847 1.634 0.000
1.270 1.720 0.000
1.693 1.703 0.000
2.117 1.634 0.000
2.540 1.497 0.000
2.963 1.273 0.000
3.387 0.963 0.000
3.810 0.602 0.000
4.233 0.241 0.000
SECTION BLOCK WIDTH, INCHES = 2.853 HEIGHT= 3.850
LEADING EDGE RADIUS = 0.172
L.E. CHORD LINE ELEVATION = 3.227
L.E. TANGENT ELEVATION = 3.207
T.E. UPPER CHORD ELEVATION = 0.156
T.E. LOWER CHORD INDENTATION= 0.184
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 10.200 BLADE ANGLE= 43.572 DEG
X YU YL
0.000 0.123 0.123
0.104 0.503 0.001
0.209 0.723 0.000
0.417 0.969 0.000
0.835 1.165 0.000
1.252 1.226 0.000
1.670 1.214 0.000
2.087 1.165 0.000
2.505 1.067 0.000
2.922 0.907 0.000
3.340 0.687 0.000
3.757 0.429 0.000
4.175 0.172 0.000
SECTION BLOCK WIDTH, INCHES = 3.092 HEIGHT= 3.344
LEADING EDGE RADIUS = 0.123
L.E. CHORD LINE ELEVATION = 2.878
L.E. TANGENT ELEVATION = 2.882
T.E. UPPER CHORD ELEVATION = 0.124
T.E. LOWER CHORD INDENTATION= 0.118
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 13.600 BLADE ANGLE= 37.319 DEG
X YU YL
0.000 0.099 0.099
0.102 0.407 0.000
0.204 0.585 0.000
0.407 0.784 0.000
0.815 0.943 0.000
1.222 0.992 0.000
1.629 0.982 0.000
2.036 0.943 0.000
2.444 0.863 0.000
2.851 0.734 0.000
3.258 0.556 0.000
3.665 0.347 0.000
4.073 0.139 0.000
SECTION BLOCK WIDTH, INCHES = 3.283 HEIGHT= 2.892
LEADING EDGE RADIUS = 0.099
L.E. CHORD LINE ELEVATION = 2.469
L.E. TANGENT ELEVATION = 2.488
T.E. UPPER CHORD ELEVATION = 0.110
T.E. LOWER CHORD INDENTATION= 0.084
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 17.000 BLADE ANGLE= 32.592 DEG
X YU YL
0.000 0.081 0.081
0.100 0.330 0.000
0.201 0.476 0.000
0.402 0.637 0.000
0.803 0.766 0.000
1.205 0.806 0.000
1.606 0.798 0.000
2.008 0.766 0.000
2.409 0.701 0.000
2.811 0.596 0.000
3.213 0.451 0.000
3.614 0.282 0.000
4.016 0.113 0.000
SECTION BLOCK WIDTH, INCHES = 3.413 HEIGHT= 2.523
LEADING EDGE RADIUS = 0.081
L.E. CHORD LINE ELEVATION = 2.163
L.E. TANGENT ELEVATION = 2.188
T.E. UPPER CHORD ELEVATION = 0.095
T.E. LOWER CHORD INDENTATION= 0.061
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 20.400 BLADE ANGLE= 28.841 DEG
X YU YL
0.000 0.065 0.065
0.097 0.269 0.000
0.194 0.386 0.000
0.389 0.517 0.000
0.778 0.622 0.000
1.167 0.655 0.000
1.556 0.648 0.000
1.945 0.622 0.000
2.333 0.570 0.000
2.722 0.485 0.000
3.111 0.367 0.000
3.500 0.229 0.000
3.889 0.092 0.000
SECTION BLOCK WIDTH, INCHES = 3.427 HEIGHT= 2.176
LEADING EDGE RADIUS = 0.065
L.E. CHORD LINE ELEVATION = 1.876
L.E. TANGENT ELEVATION = 1.902
T.E. UPPER CHORD ELEVATION = 0.080
T.E. LOWER CHORD INDENTATION= 0.044
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 23.800 BLADE ANGLE= 25.819 DEG
X YU YL
0.000 0.051 0.051
0.089 0.211 0.000
0.179 0.304 0.000
0.357 0.407 0.000
0.715 0.489 0.000
1.072 0.515 0.000
1.430 0.510 0.000
1.787 0.489 0.000
2.145 0.448 0.000
2.502 0.381 0.000
2.859 0.288 0.000
3.217 0.180 0.000
3.574 0.072 0.000
SECTION BLOCK WIDTH, INCHES = 3.232 HEIGHT= 1.795
LEADING EDGE RADIUS = 0.051
L.E. CHORD LINE ELEVATION = 1.557
L.E. TANGENT ELEVATION = 1.581
T.E. UPPER CHORD ELEVATION = 0.065
T.E. LOWER CHORD INDENTATION= 0.031
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 27.200 BLADE ANGLE= 22.965 DEG
X YU YL
0.000 0.044 0.044
0.081 0.180 0.000
0.162 0.259 0.000
0.324 0.347 0.000
0.649 0.418 0.000
0.973 0.439 0.000
1.297 0.435 0.000
1.622 0.418 0.000
1.946 0.382 0.000
2.270 0.325 0.000
2.595 0.246 0.000
2.919 0.154 0.000
3.243 0.062 0.000
SECTION BLOCK WIDTH, INCHES = 2.997 HEIGHT= 1.483
LEADING EDGE RADIUS = 0.044
L.E. CHORD LINE ELEVATION = 1.265
L.E. TANGENT ELEVATION = 1.289
T.E. UPPER CHORD ELEVATION = 0.057
T.E. LOWER CHORD INDENTATION= 0.024
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 30.600 BLADE ANGLE= 21.134 DEG
X YU YL
0.000 0.031 0.031
0.067 0.127 0.000
0.134 0.182 0.000
0.268 0.244 0.000
0.537 0.293 0.000
0.805 0.309 0.000
1.073 0.306 0.000
1.342 0.293 0.000
1.610 0.269 0.000
1.878 0.229 0.000
2.147 0.173 0.000
2.415 0.108 0.000
2.684 0.043 0.000
SECTION BLOCK WIDTH, INCHES = 2.510 HEIGHT= 1.115
LEADING EDGE RADIUS = 0.031
L.E. CHORD LINE ELEVATION = 0.968
L.E. TANGENT ELEVATION = 0.985
T.E. UPPER CHORD ELEVATION = 0.040
T.E. LOWER CHORD INDENTATION= 0.016
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 34.000 BLADE ANGLE= 19.914 DEG
X YU YL
0.000 0.019 0.019
0.053 0.078 0.000
0.106 0.112 0.000
0.211 0.150 0.000
0.422 0.181 0.000
0.633 0.190 0.000
0.844 0.189 0.000
1.056 0.181 0.000
1.267 0.166 0.000
1.478 0.141 0.000
1.689 0.107 0.000
1.900 0.067 0.000
2.111 0.027 0.000
SECTION BLOCK WIDTH, INCHES = 1.989 HEIGHT= 0.799
LEADING EDGE RADIUS = 0.019
L.E. CHORD LINE ELEVATION = 0.719
L.E. TANGENT ELEVATION = 0.730
T.E. UPPER CHORD ELEVATION = 0.025
T.E. LOWER CHORD INDENTATION= 0.009
BLADE SECTION BLOCK DIMENSIONAL SUMMARY IN INCHES
STA WIDTH HEIGHT LE RAD LE ELV CHRD ELV TE ELV TE INDT BTM ELV
6.80 2.853 3.850 0.172 3.227 3.207 0.156 0.184 0.000
10.20 3.092 3.344 0.123 2.878 2.882 0.124 0.118 0.253
13.60 3.283 2.892 0.099 2.469 2.488 0.110 0.084 0.479
17.00 3.413 2.523 0.081 2.163 2.188 0.095 0.061 0.663
20.40 3.427 2.176 0.065 1.876 1.902 0.080 0.044 0.837
23.80 3.232 1.795 0.051 1.557 1.581 0.065 0.031 1.028
27.20 2.997 1.483 0.044 1.265 1.289 0.057 0.024 1.184
30.60 2.510 1.115 0.031 0.968 0.985 0.040 0.016 1.367
34.00 1.989 0.799 0.019 0.719 0.730 0.025 0.009 1.525
OVERALL MAXIMUM SECTION BLOCK WIDTH= 3.427 HEIGHT= 3.850
NOTE: BTM ELV is the centered block, bottom elevation mark of each
section referenced to the bottom of the tallest section block. All other
elevations are referenced to their own section block bottom. TE INDT is
the trailing edge mark on the bottom of each section block inward from
the trailing edge vertical side. These marks should only be used as a
rough starting guide. Blade airfoil sections should be completed using
angle templates to get blade angle correct and airfoil templates to get
leading edge radius and surface curvature correct for each section.
NOTE: Blade chord angle is measured from the plane of rotation. The
chord line is along the flat bottom of the airfoil. Airfoil coordinates
are measured along the chord line from the leading edge (X) and
perpendicular to the chord line (YL = lower surface and YU = upper
surface positive up). Section block dimensions are given without
margin. Add whatever working margin you may need. The primary concern
is accurate blade angles. The block for each blade station can be
shifted in any consistent manner for alignment. If shifted forward or
aft circumferentially it will effect a slight sweep. Any sweep will tend
to increase torsional deflection under load and reduce performance. Each
block could be centered on a line through the center of the hub. A
possibly simpler and better method would be to align the bottom of each
block flat with the back of the hub and centered on a plane through the
propeller shaft. This will tend to compensate for any forward axial
coning under load. Finally, shape the leading edge radius accurately and
keep the trailing edge squared off, not rounded.
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
THRUST=DRAG 0 -0.5276E-10 SATISFIED
CRUISE SHP=HPA 0 -0.4883E-10 SATISFIED
CLIMB SHP=HPA 0 -0.4476E-10 SATISFIED
ALPHA>=ABMIN -1 21.19 SATISFIED
CLIMB RATE>=RCLM -1 0.1299E+07 SATISFIED
PAYOFF= 1884.16 (-VCRS) TRIAL RUNS = 170
PROP OPTIMIZER (tm) v1.95
Copyright 1994 Donald R Bates - All Rights Reserved
BATES ENGINEERING, 2742 Swansboro Road, Placerville, CA 95667
Phone/FAX 916-622-1886