20x12WE (20x12WE.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 1.2500 12.0000 0.0000 0.0000 0.6250 0.0000 0.3360 0.0000 0.4200 0.0000 0.1600 0.0000 0.0000 0.2600 1.1810 12.0000 0.0409 -0.6883 0.6153 0.0208 0.3295 1.4326 0.3892 0.4310 0.1763 0.0225 -0.0375 0.5200 1.1340 12.0000 0.3154 -1.1843 0.6115 0.0764 0.3100 5.5135 0.3516 0.4201 0.2174 0.0468 -0.0138 0.7800 1.1171 12.0000 1.0084 -1.1305 0.6129 0.1575 0.2846 11.6266 0.3179 0.4002 0.2768 0.0695 0.0237 1.0400 1.1371 12.0000 2.2154 -0.2932 0.6186 0.2551 0.2609 18.7286 0.2966 0.3756 0.3496 0.0895 0.0716 1.3000 1.1942 12.0000 3.9134 1.3804 0.6278 0.3602 0.2389 25.5991 0.2853 0.3490 0.4304 0.1063 0.1265 1.5600 1.2803 12.0000 5.9545 3.7397 0.6396 0.4639 0.2186 31.2786 0.2799 0.3224 0.5127 0.1193 0.1849 1.8200 1.3826 12.0000 8.0898 6.3364 0.6532 0.5571 0.2000 35.2771 0.2766 0.2973 0.5895 0.1283 0.2426 2.0800 1.4870 12.0000 10.0123 8.6458 0.6677 0.6308 0.1831 37.4560 0.2723 0.2755 0.6527 0.1323 0.2943 2.3400 1.5811 12.0000 11.4074 10.3479 0.6823 0.6760 0.1680 37.8069 0.2655 0.2591 0.6926 0.1293 0.3325 2.6000 1.6563 12.0000 11.9948 11.1492 0.6961 0.6838 0.1544 36.2877 0.2558 0.2515 0.6998 0.1147 0.3475 2.8584 1.7125 12.0000 12.0000 11.2776 0.7073 0.6653 0.1427 33.7493 0.2443 0.2507 0.6843 0.0902 0.3433 3.0890 1.7516 12.0000 12.0000 11.3737 0.7137 0.6481 0.1336 31.7279 0.2339 0.2493 0.6703 0.0683 0.3386 3.3179 1.7806 12.0000 12.0000 11.4560 0.7168 0.6308 0.1258 29.9255 0.2240 0.2478 0.6563 0.0464 0.3331 3.5469 1.8003 12.0000 12.0000 11.5232 0.7169 0.6131 0.1193 28.3007 0.2148 0.2464 0.6424 0.0247 0.3267 3.7759 1.8113 12.0000 12.0000 11.5727 0.7141 0.5953 0.1141 26.8306 0.2067 0.2454 0.6284 0.0035 0.3197 4.0048 1.8139 12.0000 12.0000 11.6018 0.7086 0.5772 0.1102 25.4960 0.1999 0.2447 0.6144 -0.0167 0.3125 4.2338 1.8088 12.0000 12.0000 11.6070 0.7004 0.5592 0.1075 24.2801 0.1945 0.2444 0.6005 -0.0356 0.3053 4.4628 1.7963 12.0000 12.0000 11.5840 0.6897 0.5413 0.1061 23.1687 0.1906 0.2442 0.5865 -0.0526 0.2987 4.6917 1.7770 12.0000 12.0000 11.5463 0.6767 0.5238 0.1055 22.1498 0.1875 0.2432 0.5727 -0.0676 0.2928 4.9207 1.7514 12.0000 12.0000 11.5087 0.6615 0.5070 0.1050 21.2126 0.1839 0.2397 0.5588 -0.0808 0.2879 5.1497 1.7199 12.0000 12.0000 11.4736 0.6443 0.4910 0.1045 20.3484 0.1797 0.2336 0.5450 -0.0918 0.2841 5.3786 1.6831 12.0000 12.0000 11.4431 0.6251 0.4758 0.1040 19.5491 0.1750 0.2252 0.5311 -0.1009 0.2815 5.6076 1.6414 12.0000 12.0000 11.4160 0.6041 0.4613 0.1035 18.8081 0.1699 0.2146 0.5173 -0.1079 0.2798 5.8366 1.5954 12.0000 12.0000 11.3932 0.5815 0.4474 0.1031 18.1193 0.1645 0.2023 0.5034 -0.1130 0.2790 6.0655 1.5454 12.0000 12.0000 11.3724 0.5574 0.4339 0.1027 17.4777 0.1587 0.1893 0.4894 -0.1173 0.2781 6.2945 1.4921 12.0000 12.0000 11.3520 0.5320 0.4206 0.1023 16.8787 0.1527 0.1760 0.4755 -0.1212 0.2769 6.5234 1.4358 12.0000 12.0000 11.3321 0.5053 0.4076 0.1020 16.3184 0.1464 0.1627 0.4616 -0.1248 0.2752 6.7524 1.3771 12.0000 12.0000 11.3127 0.4776 0.3948 0.1016 15.7931 0.1400 0.1494 0.4477 -0.1282 0.2732 6.9814 1.3165 12.0000 12.0000 11.2939 0.4489 0.3822 0.1013 15.2998 0.1334 0.1363 0.4338 -0.1315 0.2707 7.2103 1.2545 12.0000 12.0000 11.2756 0.4195 0.3697 0.1011 14.8357 0.1268 0.1236 0.4199 -0.1348 0.2679 7.4393 1.1915 12.0000 12.0000 11.2580 0.3894 0.3574 0.1008 14.3983 0.1201 0.1114 0.4060 -0.1381 0.2646 7.6683 1.1280 12.0000 12.0000 11.2411 0.3587 0.3453 0.1006 13.9855 0.1135 0.0997 0.3921 -0.1416 0.2608 7.8972 1.0646 12.0000 12.0000 11.2247 0.3278 0.3332 0.1004 13.5953 0.1069 0.0888 0.3781 -0.1453 0.2566 8.1262 1.0017 12.0000 12.0000 11.2088 0.2965 0.3213 0.1003 13.2259 0.1005 0.0786 0.3642 -0.1494 0.2519 8.3552 0.9398 12.0000 12.0000 11.1937 0.2652 0.3094 0.1001 12.8757 0.0941 0.0692 0.3503 -0.1539 0.2467 8.5841 0.8794 12.0000 12.0000 11.1791 0.2340 0.2975 0.1000 12.5433 0.0880 0.0606 0.3364 -0.1589 0.2410 8.8131 0.8210 12.0000 12.0000 11.1652 0.2029 0.2857 0.1000 12.2273 0.0821 0.0528 0.3225 -0.1644 0.2348 9.0421 0.7651 12.0000 12.0000 11.1517 0.1722 0.2738 0.0999 11.9267 0.0764 0.0459 0.3086 -0.1707 0.2281 9.2710 0.7121 12.0000 12.0000 11.1383 0.1419 0.2618 0.0999 11.6403 0.0711 0.0398 0.2947 -0.1777 0.2208 9.4907 0.6645 12.0000 12.0000 11.1250 0.1135 0.2503 0.0999 11.3780 0.0664 0.0347 0.2813 -0.1852 0.2133 9.5505 0.6522 12.0000 12.0000 11.1112 0.1059 0.2471 0.0999 11.3085 0.0652 0.0334 0.2775 -0.1874 0.2110 9.6010 0.6393 12.0000 12.0000 11.0772 0.0968 0.2439 0.0999 11.2506 0.0639 0.0321 0.2733 -0.1907 0.2082 9.6515 0.6202 12.0000 12.0000 11.0215 0.0815 0.2394 0.0999 11.1932 0.0620 0.0303 0.2674 -0.1975 0.2042 9.7020 0.5943 12.0000 12.0000 10.9468 0.0594 0.2337 0.0999 11.1364 0.0594 0.0278 0.2595 -0.2081 0.1990 9.7525 0.5603 12.0000 12.0000 10.8558 0.0291 0.2263 0.0999 11.0801 0.0560 0.0247 0.2495 -0.2232 0.1923 9.8030 0.5159 12.0000 12.0000 10.5534 -0.0115 0.2169 0.0999 11.0245 0.0516 0.0210 0.2371 -0.2441 0.1842 9.8535 0.4566 12.0000 12.0000 10.0730 -0.0669 0.2048 0.1000 10.9693 0.0456 0.0165 0.2214 -0.2732 0.1743 9.9040 0.3696 12.0000 12.0000 9.6160 -0.1498 0.1874 0.1000 10.9147 0.0369 0.0108 0.1998 -0.3174 0.1611 9.9545 0.2032 12.0000 12.0000 9.8251 -0.3108 0.1551 0.1000 10.8607 0.0203 0.0033 0.1613 -0.4045 0.1395 10.0000 0.0284 12.0000 12.0061 12.0060 -0.4805 0.1217 0.1000 10.8178 0.0028 0.0000 0.1217 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.60 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.254681 TOTAL WEIGHT (Kg) = 0.115502 TOTAL VOLUME (IN**3) = 4.149083 TOTAL PROJECTED AREA (IN**2) = 24.6145 MOMENT OF INERTIA (SNAIL-IN**2) = 0.011883 MOMENT OF INERTIA (Kg-M**2) = 0.001342 STATIC MOMENT, ONE SIDE (IN-LB) = 0.441741 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 = 80.006 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6057.65 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.60, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412