This is the data generated by the Bates program. It is a bit difficult
to interpret, but the important parts are the table titled 'Propellor Blade
Shape' which helps you to construct the planform and set the blade
angles and the individual blade profiles. You do not really need to
plot each template (spaced at 1/10th radius). Nigel gets by using stations
4, 7 and 10.
LONG EZE Lee Devlin Prop Design 3 Blade
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=60,120
abmin=1.55 @ cldes=.4
DMAX= 64
RCLM=1
END
DESVAR
@ afdes=80
REDFAC=1.0
DIAM=64 PITCH=66
NB=3
RPMCRS=2600 ALTCRS=1000
DREF=70
WT0=920
WPAYLD=350
SPAN=26
OSWALD=.851
SFCLM=1
sfcrs=.1
pctpwr=100
VCRS=170
RPMCLM=5000
VCLM=100 ALTCLM=300
KS=1.00
ADRAG=2.1
VCLM=100 RPMCLM=5000
END
TABLES
STA=.2,.3,.4,.5,.6,.7,.8,.9,1.
CHORD=5.217 5.138 5.090 5.023 4.852 4.527 4.080 3.424 2.651
TCTAB=.4064 .2937 .2436 .2007 .1684 .1440 .1355 .1151 .0902
RPMTAB=1800 2250 2700
HPTAB= 79 98 108
SFCTAB= .60 .58 .55
END
EOF
LONG EZE Lee Devlin Prop Design 3 Blade
@ 10/19/97 21:07:27.42
>>>> OPTIMIZED DESIGN:
VARIABLE INITIALLY OPTIMIZED LOWER LIMIT UPPER LIMIT
AFDES 93.2953 66.1400 60.0000 120.000
DIAM 64.0000 64.0000 12.8000 64.0000
PITCH 66.0000 58.1375 33.0000 132.000
RPMCRS 2600.00 2700.00 1800.00 2700.00
VCRS 170.000 177.907 127.500 212.500
RPMCLM 2700.00 2233.60 1800.00 2700.00
VCLM 100.000 100.728 75.0000 125.000
PROPELLER DESIGN CRUISE PERFORMANCE, ALT= 1000.00 FT
NUMBER OF BLADES = 3 VELOCITY, MPH = 177.91
BLADE ACTIVITY FACTOR= 66.14 THRUST, POUNDS = 183.14
DIAMETER, INCHES = 64.00 DRAG, POUNDS = 183.14
GEOMETRIC PITCH, IN = 58.14 EFFECTIVE PITCH, IN = 69.58
ABSOLUTE PITCH, IN = 74.59 THRUST HP = 86.89
BLADE ANGLE DEG @75%R= 26.32 SHAFT HP = 104.25
ALPHA @ 0LL DEG @75%R= 1.55 HP AVAILABLE = 104.25
DESIGN LIFT COEF, CL = 0.2399 PROPELLER RPM = 2700.00
THRUST COEF, CT = 0.0484 ENGINE RPM = 2700.00
POWER COEF, CP = 0.0632 REDUCT FACTOR = 1.00
ADVANCE RATIO, J = 1.0872 PARASITE DRAG,LB = 165.02
EFFICIENCY, ETA = 0.8334 INDUCED DRAG, LB = 11.36
ETA COMPRESS CORRECT.= 0.00% SLIPSTREAM DRAG = 6.76
ETA PROFILE DRAG CORR= 0.29% SFC, LB/HP/HR = 0.55
ETA DIAMETER CORRECT.= -1.30% MILES/GALLON = 18.62
FUEL FLOW, GPH = 9.56
SLIPSTREAM COEF, KS = 1.0000 SOUND SPEED,FPS = 1112.61
ADRAG, SQ FT = 2.100 TIP SPEED, FPS = 797.86
GROSS WEIGHT, LB = 1270.0 TIP MACH NUMBER = 0.72
WPAYLD, LB = 350.0 CAFE CHALLENGE = 526744.
CLIMB PERFORMANCE AT V= 100.73 MPH, ALTITUDE= 300.00
NUMBER OF BLADES = 3 CLIMB RATE, FPM = 1201.46
BLADE ACTIVITY FACTOR= 66.14 THRUST, POUNDS = 270.84
DIAMETER, INCHES = 64.00 DRAG, POUNDS = 98.70
EFFECTIVE PITCH, IN = 47.62 THRUST HP = 72.75
BLADE ALPHA DEG @75%R= 8.79 SHAFT HP = 96.41
BLADE LIFT COEF, CL = 0.9644 HP AVAILABLE = 96.41
PROPELLER RPM = 2233.60
THRUST COEF, CT = 0.1025 ENGINE RPM = 2233.60
POWER COEF, CP = 0.1011 PARASITE DRAG,LB = 54.00
ADVANCE RATIO, J = 0.7441 INDUCED DRAG, LB = 34.71
EFFICIENCY, ETA = 0.7546 SLIPSTREAM DRAG = 10.00
ETA COMPRESS CORRECT.= 0.00% GROSS WEIGHT, LB = 1270.00
ETA PROFILE DRAG CORR= 0.06% SOUND SPEED,FPS = 1115.30
ETA DIAMETER CORRECT.= -1.30% TIP SPEED, FPS = 641.00
ADRAG, SQ FT = 2.100 TIP MACH NUMBER = 0.57
PROPELLER BLADE SHAPE
_____STATION_____ CHORD ___THICKNESS___ CHORD ANGLE ___LOCAL___
R/R(TIP) INCHES INCHES RATIO INCHES DEGREES MACH REYN
0.2000 6.40 3.70 0.4064 1.50 46.26 0.143 3.1E+05
0.3000 9.60 3.64 0.2937 1.07 39.60 0.215 4.5E+05
0.4000 12.80 3.61 0.2436 0.88 33.27 0.287 6.0E+05
0.5000 16.00 3.56 0.2007 0.71 28.70 0.359 7.4E+05
0.6000 19.20 3.44 0.1684 0.58 25.20 0.430 8.6E+05
0.7000 22.40 3.21 0.1440 0.46 22.45 0.502 9.3E+05
0.8000 25.60 2.89 0.1355 0.39 19.85 0.574 9.6E+05
0.9000 28.80 2.43 0.1151 0.28 18.26 0.645 9.1E+05
1.0000 32.00 1.88 0.0902 0.17 17.25 0.717 7.8E+05
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 6.400 BLADE ANGLE= 46.263 DEG
X YU YL
0.000 0.150 0.150
0.092 0.616 0.012
0.185 0.887 0.000
0.370 1.187 0.000
0.740 1.428 0.000
1.110 1.503 0.000
1.479 1.488 0.000
1.849 1.428 0.000
2.219 1.308 0.000
2.589 1.112 0.000
2.959 0.842 0.000
3.329 0.526 0.000
3.698 0.210 0.000
SECTION BLOCK WIDTH, INCHES = 2.647 HEIGHT= 3.288
LEADING EDGE RADIUS = 0.150
L.E. CHORD LINE ELEVATION = 2.672
L.E. TANGENT ELEVATION = 2.668
T.E. UPPER CHORD ELEVATION = 0.145
T.E. LOWER CHORD INDENTATION= 0.152
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 9.600 BLADE ANGLE= 39.599 DEG
X YU YL
0.000 0.107 0.107
0.091 0.439 0.001
0.182 0.631 0.000
0.364 0.845 0.000
0.728 1.016 0.000
1.093 1.070 0.000
1.457 1.059 0.000
1.821 1.016 0.000
2.185 0.931 0.000
2.550 0.792 0.000
2.914 0.599 0.000
3.278 0.374 0.000
3.642 0.150 0.000
SECTION BLOCK WIDTH, INCHES = 2.858 HEIGHT= 2.790
LEADING EDGE RADIUS = 0.107
L.E. CHORD LINE ELEVATION = 2.322
L.E. TANGENT ELEVATION = 2.336
T.E. UPPER CHORD ELEVATION = 0.115
T.E. LOWER CHORD INDENTATION= 0.095
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 12.800 BLADE ANGLE= 33.267 DEG
X YU YL
0.000 0.088 0.088
0.090 0.360 0.000
0.180 0.519 0.000
0.361 0.694 0.000
0.722 0.835 0.000
1.083 0.879 0.000
1.443 0.870 0.000
1.804 0.835 0.000
2.165 0.765 0.000
2.526 0.650 0.000
2.887 0.492 0.000
3.248 0.308 0.000
3.608 0.123 0.000
SECTION BLOCK WIDTH, INCHES = 3.051 HEIGHT= 2.406
LEADING EDGE RADIUS = 0.088
L.E. CHORD LINE ELEVATION = 1.979
L.E. TANGENT ELEVATION = 2.005
T.E. UPPER CHORD ELEVATION = 0.103
T.E. LOWER CHORD INDENTATION= 0.068
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 16.000 BLADE ANGLE= 28.701 DEG
X YU YL
0.000 0.071 0.071
0.089 0.293 0.000
0.178 0.422 0.000
0.356 0.565 0.000
0.712 0.679 0.000
1.068 0.715 0.000
1.424 0.708 0.000
1.780 0.679 0.000
2.137 0.622 0.000
2.493 0.529 0.000
2.849 0.400 0.000
3.205 0.250 0.000
3.561 0.100 0.000
SECTION BLOCK WIDTH, INCHES = 3.146 HEIGHT= 2.071
LEADING EDGE RADIUS = 0.071
L.E. CHORD LINE ELEVATION = 1.710
L.E. TANGENT ELEVATION = 1.738
T.E. UPPER CHORD ELEVATION = 0.088
T.E. LOWER CHORD INDENTATION= 0.048
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 19.200 BLADE ANGLE= 25.201 DEG
X YU YL
0.000 0.058 0.058
0.086 0.237 0.000
0.172 0.342 0.000
0.344 0.458 0.000
0.688 0.550 0.000
1.032 0.579 0.000
1.376 0.573 0.000
1.720 0.550 0.000
2.064 0.504 0.000
2.408 0.429 0.000
2.752 0.324 0.000
3.096 0.203 0.000
3.440 0.081 0.000
SECTION BLOCK WIDTH, INCHES = 3.128 HEIGHT= 1.763
LEADING EDGE RADIUS = 0.058
L.E. CHORD LINE ELEVATION = 1.465
L.E. TANGENT ELEVATION = 1.492
T.E. UPPER CHORD ELEVATION = 0.073
T.E. LOWER CHORD INDENTATION= 0.035
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 22.400 BLADE ANGLE= 22.449 DEG
X YU YL
0.000 0.046 0.046
0.080 0.189 0.000
0.160 0.273 0.000
0.321 0.365 0.000
0.642 0.439 0.000
0.963 0.462 0.000
1.284 0.458 0.000
1.605 0.439 0.000
1.926 0.402 0.000
2.247 0.342 0.000
2.567 0.259 0.000
2.888 0.162 0.000
3.209 0.065 0.000
SECTION BLOCK WIDTH, INCHES = 2.977 HEIGHT= 1.466
LEADING EDGE RADIUS = 0.046
L.E. CHORD LINE ELEVATION = 1.226
L.E. TANGENT ELEVATION = 1.251
T.E. UPPER CHORD ELEVATION = 0.060
T.E. LOWER CHORD INDENTATION= 0.025
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 25.600 BLADE ANGLE= 19.854 DEG
X YU YL
0.000 0.039 0.039
0.072 0.161 0.000
0.145 0.231 0.000
0.289 0.310 0.000
0.578 0.372 0.000
0.868 0.392 0.000
1.157 0.388 0.000
1.446 0.372 0.000
1.735 0.341 0.000
2.025 0.290 0.000
2.314 0.219 0.000
2.603 0.137 0.000
2.892 0.055 0.000
SECTION BLOCK WIDTH, INCHES = 2.728 HEIGHT= 1.197
LEADING EDGE RADIUS = 0.039
L.E. CHORD LINE ELEVATION = 0.982
L.E. TANGENT ELEVATION = 1.006
T.E. UPPER CHORD ELEVATION = 0.052
T.E. LOWER CHORD INDENTATION= 0.019
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 28.800 BLADE ANGLE= 18.260 DEG
X YU YL
0.000 0.028 0.028
0.061 0.115 0.000
0.121 0.165 0.000
0.243 0.221 0.000
0.485 0.265 0.000
0.728 0.279 0.000
0.971 0.277 0.000
1.214 0.265 0.000
1.456 0.243 0.000
1.699 0.207 0.000
1.942 0.156 0.000
2.185 0.098 0.000
2.427 0.039 0.000
SECTION BLOCK WIDTH, INCHES = 2.310 HEIGHT= 0.910
LEADING EDGE RADIUS = 0.028
L.E. CHORD LINE ELEVATION = 0.761
L.E. TANGENT ELEVATION = 0.778
T.E. UPPER CHORD ELEVATION = 0.037
T.E. LOWER CHORD INDENTATION= 0.012
BLADE AIRFOIL COORDINATES
R.A.F. 6 BLADE STATION= 32.000 BLADE ANGLE= 17.252 DEG
X YU YL
0.000 0.017 0.017
0.047 0.070 0.000
0.094 0.100 0.000
0.188 0.134 0.000
0.376 0.161 0.000
0.564 0.170 0.000
0.752 0.168 0.000
0.940 0.161 0.000
1.128 0.147 0.000
1.316 0.125 0.000
1.504 0.095 0.000
1.691 0.059 0.000
1.879 0.024 0.000
SECTION BLOCK WIDTH, INCHES = 1.798 HEIGHT= 0.639
LEADING EDGE RADIUS = 0.017
L.E. CHORD LINE ELEVATION = 0.557
L.E. TANGENT ELEVATION = 0.569
T.E. UPPER CHORD ELEVATION = 0.023
T.E. LOWER CHORD INDENTATION= 0.007
BLADE SECTION BLOCK DIMENSIONAL SUMMARY IN INCHES
STA WIDTH HEIGHT LE RAD LE ELV CHRD ELV TE ELV TE INDT BTM ELV
6.40 2.647 3.288 0.150 2.672 2.668 0.145 0.152 0.000
9.60 2.858 2.790 0.107 2.322 2.336 0.115 0.095 0.249
12.80 3.051 2.406 0.088 1.979 2.005 0.103 0.068 0.441
16.00 3.146 2.071 0.071 1.710 1.738 0.088 0.048 0.608
19.20 3.128 1.763 0.058 1.465 1.492 0.073 0.035 0.762
22.40 2.977 1.466 0.046 1.226 1.251 0.060 0.025 0.911
25.60 2.728 1.197 0.039 0.982 1.006 0.052 0.019 1.045
28.80 2.310 0.910 0.028 0.761 0.778 0.037 0.012 1.189
32.00 1.798 0.639 0.017 0.557 0.569 0.023 0.007 1.324
OVERALL MAXIMUM SECTION BLOCK WIDTH= 3.146 HEIGHT= 3.288
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 -0.1552E-12 SATISFIED
CRUISE SHP=HPA 0 -0.2197E-12 SATISFIED
CLIMB SHP=HPA 0 -0.1098E-11 SATISFIED
ALPHA>=ABMIN -1 0.6661E-12 SATISFIED
CLIMB RATE>=RCLM -1 0.1200E+07 SATISFIED
PAYOFF= 3157.42 (-VCRS) TRIAL RUNS = 267
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