20x8W (20x8W.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 2.0000 1.7234 0.0000 0.0000 1.0000 0.0000 -0.3626 0.0000 -0.7251 0.0000 0.2000 0.0000 0.0000 0.2844 1.9130 2.4285 0.0173 -0.4465 0.9845 0.0117 -0.2119 0.5557 -0.4054 0.7416 0.2111 0.0266 -0.0173 0.5689 1.8257 3.0896 0.1342 -0.8297 0.9676 0.0426 -0.0867 2.1496 -0.1582 0.7266 0.2403 0.0573 -0.0030 0.8533 1.7434 3.7070 0.4363 -1.0276 0.9505 0.0874 0.0152 4.6525 0.0266 0.7058 0.2824 0.0895 0.0185 1.1377 1.6715 4.2804 0.9891 -0.9385 0.9347 0.1408 0.0958 7.8775 0.1602 0.6806 0.3327 0.1218 0.0451 1.4222 1.6142 4.8101 1.8263 -0.4926 0.9213 0.1976 0.1572 11.5510 0.2538 0.6525 0.3863 0.1530 0.0748 1.7066 1.5740 5.2958 2.9352 0.3299 0.9117 0.2526 0.2014 15.3090 0.3171 0.6232 0.4381 0.1824 0.1051 1.9910 1.5508 5.7378 4.2407 1.4780 0.9071 0.3006 0.2305 18.7261 0.3575 0.5940 0.4831 0.2094 0.1333 2.2754 1.5421 6.1358 5.5932 2.8124 0.9089 0.3363 0.2465 21.3663 0.3802 0.5660 0.5161 0.2336 0.1562 2.5599 1.5444 6.4901 6.7705 4.1002 0.9183 0.3546 0.2515 22.8283 0.3885 0.5398 0.5318 0.2546 0.1705 2.8443 1.5548 6.8004 7.4998 5.0338 0.9367 0.3502 0.2476 22.7658 0.3850 0.5153 0.5249 0.2718 0.1724 3.1254 1.5697 7.0640 7.8090 5.5851 0.9606 0.3331 0.2369 21.6858 0.3719 0.4883 0.5026 0.2865 0.1668 3.3484 1.5815 7.2428 8.0050 5.9847 0.9794 0.3236 0.2250 20.8311 0.3558 0.4617 0.4847 0.2985 0.1640 3.5681 1.5927 7.3924 8.1583 6.3434 0.9974 0.3166 0.2112 19.9963 0.3364 0.4325 0.4670 0.3103 0.1621 3.7878 1.6032 7.5162 8.2742 6.6641 1.0147 0.3109 0.1965 19.1705 0.3150 0.4017 0.4493 0.3219 0.1607 4.0075 1.6127 7.6253 8.3669 6.9541 1.0311 0.3056 0.1817 18.3808 0.2931 0.3708 0.4316 0.3330 0.1590 4.2272 1.6209 7.7262 8.4471 7.2174 1.0463 0.2996 0.1678 17.6425 0.2720 0.3415 0.4138 0.3436 0.1561 4.4469 1.6275 7.8189 8.5205 7.4524 1.0602 0.2919 0.1558 16.9590 0.2536 0.3158 0.3960 0.3533 0.1517 4.6666 1.6322 7.9034 8.5937 7.6577 1.0724 0.2814 0.1466 16.3353 0.2392 0.2954 0.3782 0.3623 0.1451 4.8863 1.6346 7.9796 8.6748 7.8320 1.0828 0.2672 0.1411 15.7777 0.2306 0.2823 0.3603 0.3704 0.1358 5.1060 1.6346 8.0475 8.7691 7.9740 1.0912 0.2488 0.1397 15.2874 0.2283 0.2771 0.3424 0.3777 0.1236 5.3257 1.6317 8.1072 8.8590 8.0826 1.0972 0.2298 0.1390 14.8285 0.2269 0.2732 0.3245 0.3841 0.1108 5.5454 1.6257 8.1587 8.9404 8.1571 1.1007 0.2110 0.1384 14.3911 0.2250 0.2692 0.3065 0.3896 0.0978 5.7651 1.6162 8.2020 9.0131 8.2020 1.1015 0.1925 0.1377 13.9726 0.2226 0.2647 0.2884 0.3939 0.0848 5.9848 1.6030 8.2370 9.0770 8.2370 1.0992 0.1742 0.1371 13.5707 0.2197 0.2590 0.2704 0.3969 0.0720 6.2045 1.5858 8.2638 9.1320 8.2638 1.0938 0.1562 0.1364 13.1837 0.2163 0.2522 0.2523 0.3986 0.0595 6.4242 1.5641 8.2823 9.1779 8.2824 1.0848 0.1384 0.1357 12.8099 0.2123 0.2441 0.2342 0.3987 0.0472 6.6439 1.5378 8.2926 9.2148 8.2927 1.0723 0.1210 0.1351 12.4479 0.2077 0.2348 0.2160 0.3972 0.0352 6.8636 1.5065 8.2947 9.2424 8.2947 1.0558 0.1039 0.1344 12.0963 0.2025 0.2243 0.1978 0.3939 0.0236 7.0833 1.4700 8.2885 9.2606 8.2885 1.0351 0.0871 0.1338 11.7542 0.1966 0.2125 0.1795 0.3889 0.0123 7.3030 1.4278 8.2741 9.2692 8.2741 1.0101 0.0708 0.1331 11.4203 0.1900 0.1995 0.1613 0.3820 0.0014 7.5227 1.3796 8.2515 9.2679 8.2515 0.9806 0.0548 0.1324 11.0937 0.1827 0.1855 0.1430 0.3730 -0.0092 7.7424 1.3253 8.2206 9.2565 8.2206 0.9461 0.0392 0.1318 10.7734 0.1747 0.1704 0.1246 0.3620 -0.0193 7.9621 1.2644 8.1815 9.2344 8.1815 0.9067 0.0242 0.1311 10.4583 0.1658 0.1544 0.1062 0.3488 -0.0290 8.1818 1.1967 8.1341 9.2011 8.1341 0.8619 0.0096 0.1305 10.1475 0.1561 0.1377 0.0878 0.3333 -0.0383 8.4015 1.1219 8.0785 9.1556 8.0785 0.8117 -0.0045 0.1298 9.8396 0.1456 0.1206 0.0693 0.3154 -0.0472 8.6212 1.0395 8.0147 9.0969 8.0147 0.7557 -0.0181 0.1292 9.5331 0.1343 0.1032 0.0508 0.2950 -0.0556 8.8409 0.9494 7.9336 9.0138 7.9336 0.6937 -0.0311 0.1285 9.2169 0.1220 0.0858 0.0323 0.2721 -0.0636 9.0606 0.8513 7.8112 8.8793 7.8112 0.6255 -0.0437 0.1278 8.8650 0.1088 0.0688 0.0137 0.2465 -0.0709 9.2803 0.7447 7.6461 8.6867 7.6461 0.5509 -0.0556 0.1272 8.4733 0.0947 0.0526 -0.0049 0.2181 -0.0777 9.4912 0.6342 7.4475 8.4377 7.4475 0.4731 -0.0665 0.1265 8.0533 0.0803 0.0382 -0.0228 0.1882 -0.0839 9.5505 0.6017 7.3845 8.3893 7.3769 0.4500 -0.0691 0.1264 7.9586 0.0760 0.0344 -0.0278 0.1793 -0.0855 9.6010 0.5736 7.3284 8.4229 7.3009 0.4300 -0.0705 0.1262 7.9486 0.0724 0.0312 -0.0318 0.1715 -0.0868 9.6515 0.5451 7.2701 8.5303 7.2160 0.4096 -0.0713 0.1261 8.0070 0.0687 0.0282 -0.0357 0.1636 -0.0880 9.7020 0.5162 7.2096 8.7153 7.1273 0.3889 -0.0716 0.1259 8.1364 0.0650 0.0253 -0.0393 0.1555 -0.0892 9.7525 0.4863 7.1468 8.9812 7.0404 0.3673 -0.0715 0.1258 8.3383 0.0612 0.0225 -0.0428 0.1471 -0.0902 9.8030 0.4486 7.0817 9.3311 6.9684 0.3379 -0.0722 0.1256 8.6144 0.0563 0.0191 -0.0477 0.1344 -0.0920 9.8535 0.3980 7.0144 9.7820 6.9842 0.2960 -0.0746 0.1255 8.9784 0.0499 0.0151 -0.0548 0.1149 -0.0950 9.9040 0.3267 6.9448 10.3041 7.1692 0.2336 -0.0806 0.1253 9.4020 0.0409 0.0102 -0.0661 0.0842 -0.1001 9.9545 0.1970 6.8729 10.9073 8.2874 0.1142 -0.0974 0.1252 9.8922 0.0247 0.0038 -0.0897 0.0224 -0.1112 10.0000 0.0166 6.8064 6.8063 6.8063 -0.0555 -0.1271 0.1250 6.1825 0.0021 0.0000 -0.1271 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 1.00 HUB RADIUS (IN) HUBTRA: 2.84 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.430831 TOTAL WEIGHT (Kg) = 0.195388 TOTAL VOLUME (IN**3) = 7.018781 TOTAL PROJECTED AREA (IN**2) = 27.9371 MOMENT OF INERTIA (SNAIL-IN**2) = 0.018087 MOMENT OF INERTIA (Kg-M**2) = 0.002043 STATIC MOMENT, ONE SIDE (IN-LB) = 0.696717 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 84.747 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9503.02 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 5.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.