Attachment_A_-_Blade_Specifications.pdf

Attachment A: Blade Specifications

Figure 1 shows the blade outer surface definition and geometric tolerances. Figure 2 shows a wireframe view of the blade and the positioning of the shear webs. Figure 3 and Figure 4 show the preliminary laminate layup schedule for blade skins and shear webs and the overall arrangement of the skin panels. The blade root outer shape and structural layup will be finalized based on the final adapter geometry.

Table 2 has the airfoil nondimensional coordinates.

Figure 1. Blade outer surface definition. Geometric tolerances are specified in the Notes.

Figure 2. Wireframe views of the SUMR-D blade with positioning of the shear webs.

Sta.# Blade span

(m) Twist (deg) Chord GELCOAT RESIN TRIAX-

SKINS

ROOT-

BUILDUP SPAR-CAP TE-REINF TE-REINF-

FOAM

LE-FOAM

(LE Panel)

TE-FOAM

(TE Panel)

Inboard

WEB-DB WEB-

FOAM

TE-FOAM

(TE Panel) Outboard

Surface

Paint Parasitic resin mass

Entire blade interior and exterior surfraces

Entire blade circumference to 3.8 meter span

77 mm width spar cap on HP and LP

32 mm width

TE

reinforcement

Core material in TE

Reinforcement

Core material in

LE

Core in aft panel inboard blade region

Double bias material for shear webs

Core thickenss for shear webs

Core in aft panel in outboard blade region

Gelcoat Resin SaertexEP3

(Double Bias)

Triaxial material

(SNLTriax)

ELT-

5500/EP3

(uni-glass)

ELT-

5500/EP3

(uni-glass)

Balsa Balsa Balsa SaertexEP3

(Double Bias)

Balsa Balsa

1 0 13.52692 0.9 0.12 0.36 1 165 0.15 0 0 0 0 0.6 10 0 2 0.2 13.52692 0.9 0.12 0.36 1 100 4.5 0.1 0 0 0 0.6 10 0 3 0.4 13.52692 0.9 0.12 0.36 1 40 6 0 0 0 0.6 10 0 4 0.6 13.52692 0.9 0.12 0.36 1 20 7.15 0 0 0 0.6 10 0 5 0.8 13.52692 0.9 0.12 0.36 1 15 11.83 0 0 0 0.6 10 0 6 1 13.52692 0.9 0.12 0.36 1 10 14.56 0 0 0 0.6 10 0 7 1.6 0.12 0.36 1 14.56 0 0 0 0 8 2.2 0.12 0.36 1 5 14.56 2 2 2 0 9 2.704 13.52692 1.20114 0.12 0.36 1 4 15.68 3 3 3 0

10 3.8 0.12 0.36 1 0 16.8 7 7 7 0 11 4.2 0.12 0.36 1 0 7 7 7 0 12 4.5 0.12 0.36 1 0 7 0 13 4.842308 13.52692 1.5023 0.12 0.36 1 0 16.8 7 7 7 0.6 10 0 14 5.6 0.12 0.36 1 0 0 15 6.2 0.12 0.36 1 0 0 16 6.97922 5.9693 1.20572 0.12 0.36 1 0 16.8 7 7 7 0.6 10 0 17 9.11614 3.1699 1.02054 0.12 0.36 1 0 0 18 11.25308 1.3089 0.8969 0.12 0.36 1 0 13.44 7 7 7 0.6 10 0 19 13.39 0.4948 0.7911 0.12 0.36 1 0 20 15.52692 0 0.70642 0.12 0.36 1 0 7.92 7 7 7 0.6 10 0 21 17.66384 0 0.61332 0.12 0.36 1 0 22 19.80076 0 0.41796 0.12 0.36 1 0 1.2 7 7 7 0.6 10 0 23 20.8692 0 0.3601 0.12 0.36 1 0 0.12 0.1 7 7 7 0.6 10 0

Figure 3. Preliminary layup schedule. Both low-pressure and high-pressure shells. Thickness is in mm.

Figure 4. Cross-section schematic (not to scale).

Table 1. Airfoil non-dimensional geometric coordinates.

F1-1822-0041 F1-2040-0087 F1-2655-0262 F1-3856-0738 F1-4846-1226 x/xmax y/xmax x/xmax y/xmax x/xmax y/xmax x/xmax y/xmax x/xmax y/xmax

1.000000 0.002050 1.000000 0.004350 1.000008 0.013094 1.000000 0.036900 0.999999 0.061299

0.996287 0.003501 0.996177 0.005828 0.995749 0.014655 0.995098 0.039345 0.994692 0.063775

0.986312 0.007798 0.985929 0.010248 0.984678 0.019572 0.983113 0.046777 0.981854 0.071527

0.971360 0.013869 0.970611 0.016563 0.968653 0.026687 0.966633 0.057249 0.964382 0.082827

0.951469 0.020749 0.950269 0.023789 0.947567 0.034652 0.945394 0.068911 0.942059 0.095625

0.926465 0.028303 0.924747 0.031812 0.921111 0.043446 0.919166 0.081614 0.914757 0.109691

0.896673 0.036672 0.894414 0.040785 0.889741 0.053274 0.888427 0.095131 0.882936 0.124581

0.862592 0.045747 0.859818 0.050594 0.854062 0.064000 0.853469 0.109096 0.846744 0.139899

0.824736 0.055387 0.821518 0.061078 0.814693 0.075439 0.814795 0.123463 0.806719 0.155731

0.783655 0.065417 0.780107 0.072030 0.772270 0.087337 0.773044 0.137905 0.763590 0.171740

0.739930 0.075639 0.736201 0.083213 0.727458 0.099403 0.728816 0.152061 0.718026 0.187537

0.694169 0.085832 0.690435 0.094353 0.680912 0.111242 0.682681 0.165546 0.670664 0.202695

0.647004 0.095747 0.643453 0.105141 0.633193 0.122454 0.635192 0.177985 0.622109 0.216791

0.599080 0.105093 0.595903 0.115225 0.584809 0.132697 0.586863 0.189009 0.572929 0.229405

0.551062 0.113521 0.548444 0.124170 0.536285 0.141635 0.538183 0.198290 0.523662 0.240150

0.503498 0.120523 0.501503 0.131350 0.488090 0.148937 0.489609 0.205525 0.474809 0.248654

0.456688 0.125599 0.455216 0.136309 0.440655 0.154305 0.441568 0.210464 0.426824 0.254590

0.410789 0.128478 0.409717 0.138921 0.394342 0.157473 0.394455 0.212915 0.380122 0.257683

0.365959 0.129059 0.365194 0.139127 0.349449 0.158261 0.348655 0.212746 0.335089 0.257705

0.322349 0.127357 0.321821 0.136962 0.306248 0.156545 0.304535 0.209871 0.292046 0.254460

0.280162 0.123550 0.279817 0.132619 0.264949 0.152287 0.262435 0.204239 0.251239 0.247828

0.239713 0.117885 0.239510 0.126347 0.225723 0.145547 0.222646 0.195855 0.212855 0.237810

0.201375 0.110566 0.201275 0.118357 0.188712 0.136524 0.185429 0.184810 0.177082 0.224532

0.165510 0.101794 0.165480 0.108858 0.154134 0.125533 0.151037 0.171246 0.144123 0.208170

0.132457 0.091764 0.132467 0.098056 0.122307 0.112895 0.119699 0.155352 0.114156 0.188939

0.102521 0.080693 0.102547 0.086175 0.093545 0.098914 0.091610 0.137362 0.087316 0.167133

0.075979 0.068821 0.075999 0.073466 0.068155 0.083884 0.066932 0.117575 0.063725 0.143124

0.053080 0.056414 0.053079 0.060205 0.046408 0.068115 0.045806 0.096355 0.043494 0.117374

0.034053 0.043758 0.034023 0.046689 0.028550 0.051926 0.028365 0.074143 0.026782 0.090420

0.019103 0.031158 0.019042 0.033234 0.014793 0.035652 0.014781 0.051453 0.013817 0.062800

0.008402 0.018936 0.008321 0.020174 0.005314 0.019697 0.005301 0.028838 0.004855 0.035070

0.002076 0.007462 0.002004 0.007898 0.000309 0.004630 0.000350 0.007012 0.000296 0.007920

0.000235 -0.002465 0.000258 -0.002772 0.001049 -0.009017 0.001142 -0.014261 0.001162 -0.018797

0.004339 -0.010691 0.004581 -0.011813 0.007986 -0.022241 0.007538 -0.035895 0.007318 -0.045769

0.014880 -0.018143 0.015395 -0.020249 0.020038 -0.035843 0.018229 -0.057730 0.017661 -0.072759

0.030839 -0.025206 0.031583 -0.028392 0.036640 -0.049239 0.032853 -0.079068 0.031852 -0.099105

0.051916 -0.031744 0.052810 -0.036071 0.057458 -0.062044 0.051190 -0.099337 0.049666 -0.124237

0.077773 -0.037660 0.078721 -0.043150 0.082204 -0.073898 0.073086 -0.118044 0.070936 -0.147647

0.108067 -0.042837 0.108965 -0.049481 0.110611 -0.084473 0.098386 -0.134786 0.095486 -0.168910

0.142441 -0.047158 0.143178 -0.054922 0.142422 -0.093488 0.126914 -0.149211 0.123109 -0.187649

0.180530 -0.050519 0.180994 -0.059340 0.177360 -0.100696 0.158479 -0.161005 0.153574 -0.203517

0.221941 -0.052857 0.222016 -0.062644 0.215137 -0.105869 0.192882 -0.169896 0.186632 -0.216193

0.266239 -0.054123 0.265807 -0.064758 0.255464 -0.108789 0.229920 -0.175650 0.222029 -0.225379

0.312956 -0.054265 0.311900 -0.065601 0.298097 -0.109254 0.269398 -0.178080 0.259506 -0.230800

0.361612 -0.053229 0.359815 -0.065089 0.342857 -0.107135 0.311133 -0.177042 0.298813 -0.232187

0.411727 -0.050962 0.409073 -0.063128 0.389618 -0.102361 0.354945 -0.172439 0.339669 -0.229247

0.462783 -0.047389 0.459140 -0.059580 0.438406 -0.095077 0.400847 -0.164005 0.382185 -0.221172

0.514577 -0.042181 0.509924 -0.053949 0.489242 -0.085775 0.449266 -0.152025 0.427335 -0.208004

0.567230 -0.035613 0.561768 -0.046511 0.541800 -0.075140 0.500363 -0.137494 0.475764 -0.191010

0.620412 -0.028559 0.614449 -0.038325 0.595496 -0.063846 0.553741 -0.121336 0.527295 -0.171299

0.673360 -0.021569 0.667217 -0.030046 0.649636 -0.052543 0.608857 -0.104509 0.581617 -0.150073

0.725259 -0.015092 0.719260 -0.022224 0.703394 -0.041842 0.664946 -0.088004 0.638140 -0.128663

0.775233 -0.009489 0.769678 -0.015315 0.755821 -0.032298 0.720996 -0.072793 0.695917 -0.108460

0.822363 -0.005029 0.817502 -0.009676 0.805861 -0.024351 0.775741 -0.059721 0.753596 -0.090766

0.865710 -0.001865 0.861724 -0.005528 0.852380 -0.018297 0.827695 -0.049417 0.809425 -0.076635

0.904346 -0.000026 0.901327 -0.002949 0.894218 -0.014234 0.875231 -0.042173 0.861356 -0.066668

0.937382 0.000607 0.935323 -0.001835 0.930232 -0.012033 0.916663 -0.037857 0.907173 -0.060852

0.964124 0.000313 0.962926 -0.001893 0.959521 -0.011247 0.950769 -0.035660 0.945158 -0.058230

0.983819 -0.000627 0.983285 -0.002799 0.981426 -0.011495 0.976855 -0.035078 0.974275 -0.058035

0.995912 -0.001592 0.995781 -0.003841 0.995250 -0.012435 0.993968 -0.035987 0.993328 -0.059870

1.000000 -0.002050 1.000000 -0.004350 0.999992 -0.013094 1.000000 -0.036900 1.000002 -0.061298

Attachment A: Blade Specifications