20.5x12WE (205x12WE.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 0.3200 0.0000 0.4000 0.0000 0.1200 0.0000 0.0000 0.2730 1.1814 12.0000 0.0459 -0.7788 0.6156 0.0213 0.3183 1.5326 0.3760 0.4140 0.1386 0.0213 -0.0640 0.5460 1.1426 12.0000 0.3511 -1.3462 0.6140 0.0784 0.3132 5.8430 0.3579 0.4144 0.1879 0.0459 -0.0387 0.8190 1.1410 12.0000 1.1073 -1.3251 0.6190 0.1618 0.3047 12.1438 0.3477 0.4103 0.2600 0.0686 0.0018 1.0920 1.1817 12.0000 2.3914 -0.4922 0.6292 0.2624 0.2928 19.2150 0.3460 0.4034 0.3470 0.0883 0.0546 1.3650 1.2621 12.0000 4.1451 1.1717 0.6434 0.3710 0.2775 25.7945 0.3502 0.3942 0.4413 0.1046 0.1164 1.6380 1.3715 12.0000 6.1916 3.4885 0.6604 0.4785 0.2588 31.0313 0.3549 0.3822 0.5345 0.1170 0.1832 1.9110 1.4951 12.0000 8.2772 6.0120 0.6789 0.5758 0.2367 34.5807 0.3538 0.3664 0.6185 0.1253 0.2500 2.1840 1.6178 12.0000 10.1185 8.2845 0.6976 0.6536 0.2112 36.4037 0.3416 0.3455 0.6854 0.1285 0.3104 2.4570 1.7263 12.0000 11.4398 10.0192 0.7154 0.7027 0.1822 36.5395 0.3146 0.3184 0.7270 0.1243 0.3558 2.7300 1.8109 12.0000 11.9950 11.0183 0.7310 0.7142 0.1499 34.9648 0.2715 0.2841 0.7347 0.1077 0.3755 3.0009 1.8724 12.0000 12.0000 11.3580 0.7427 0.6976 0.1248 32.4741 0.2337 0.2579 0.7185 0.0793 0.3723 3.2352 1.9140 12.0000 12.0000 11.4132 0.7493 0.6796 0.1191 30.5548 0.2280 0.2615 0.7042 0.0559 0.3664 3.4674 1.9452 12.0000 12.0000 11.4206 0.7526 0.6606 0.1167 28.8458 0.2271 0.2703 0.6901 0.0327 0.3589 3.6997 1.9670 12.0000 12.0000 11.4287 0.7530 0.6413 0.1145 27.3039 0.2252 0.2779 0.6759 0.0092 0.3503 3.9319 1.9797 12.0000 12.0000 11.4365 0.7505 0.6220 0.1123 25.9075 0.2224 0.2843 0.6618 -0.0141 0.3411 4.1641 1.9838 12.0000 12.0000 11.4427 0.7453 0.6029 0.1103 24.6384 0.2189 0.2889 0.6476 -0.0367 0.3319 4.3963 1.9799 12.0000 12.0000 11.4447 0.7375 0.5842 0.1084 23.4811 0.2147 0.2913 0.6335 -0.0578 0.3233 4.6286 1.9685 12.0000 12.0000 11.4344 0.7273 0.5661 0.1066 22.4222 0.2099 0.2913 0.6194 -0.0770 0.3156 4.8608 1.9500 12.0000 12.0000 11.4104 0.7147 0.5487 0.1049 21.4504 0.2046 0.2886 0.6053 -0.0938 0.3091 5.0930 1.9249 12.0000 12.0000 11.3838 0.6999 0.5321 0.1034 20.5558 0.1990 0.2829 0.5913 -0.1081 0.3041 5.3252 1.8936 12.0000 12.0000 11.3578 0.6831 0.5162 0.1019 19.7300 0.1931 0.2744 0.5773 -0.1197 0.3005 5.5575 1.8568 12.0000 12.0000 11.3328 0.6643 0.5012 0.1006 18.9656 0.1868 0.2632 0.5632 -0.1284 0.2985 5.7897 1.8147 12.0000 12.0000 11.3106 0.6437 0.4870 0.0994 18.2563 0.1804 0.2497 0.5491 -0.1344 0.2977 6.0219 1.7681 12.0000 12.0000 11.2906 0.6215 0.4731 0.0983 17.5965 0.1738 0.2351 0.5350 -0.1390 0.2972 6.2541 1.7172 12.0000 12.0000 11.2701 0.5978 0.4596 0.0973 16.9814 0.1672 0.2202 0.5209 -0.1430 0.2964 6.4864 1.6627 12.0000 12.0000 11.2487 0.5726 0.4462 0.0965 16.4067 0.1604 0.2051 0.5068 -0.1464 0.2952 6.7186 1.6049 12.0000 12.0000 11.2265 0.5462 0.4331 0.0957 15.8686 0.1537 0.1900 0.4927 -0.1493 0.2936 6.9508 1.5444 12.0000 12.0000 11.2036 0.5187 0.4202 0.0951 15.3639 0.1469 0.1751 0.4785 -0.1520 0.2917 7.1830 1.4817 12.0000 12.0000 11.1800 0.4901 0.4074 0.0946 14.8896 0.1402 0.1605 0.4644 -0.1544 0.2894 7.4153 1.4172 12.0000 12.0000 11.1555 0.4608 0.3948 0.0942 14.4431 0.1335 0.1464 0.4503 -0.1567 0.2866 7.6475 1.3514 12.0000 12.0000 11.1301 0.4306 0.3824 0.0939 14.0221 0.1269 0.1328 0.4362 -0.1589 0.2834 7.8797 1.2849 12.0000 12.0000 11.1035 0.3999 0.3700 0.0938 13.6244 0.1205 0.1199 0.4221 -0.1613 0.2798 8.1119 1.2180 12.0000 12.0000 11.0757 0.3687 0.3578 0.0937 13.2483 0.1142 0.1077 0.4080 -0.1638 0.2757 8.3442 1.1513 12.0000 12.0000 11.0466 0.3372 0.3456 0.0938 12.8921 0.1080 0.0963 0.3939 -0.1665 0.2711 8.5764 1.0852 12.0000 12.0000 11.0160 0.3055 0.3335 0.0940 12.5543 0.1020 0.0857 0.3798 -0.1697 0.2661 8.8086 1.0203 12.0000 12.0000 10.9837 0.2737 0.3214 0.0943 12.2334 0.0962 0.0759 0.3657 -0.1732 0.2605 9.0408 0.9570 12.0000 12.0000 10.9495 0.2420 0.3094 0.0947 11.9283 0.0907 0.0670 0.3516 -0.1774 0.2545 9.2731 0.8958 12.0000 12.0000 10.9131 0.2105 0.2973 0.0953 11.6378 0.0853 0.0589 0.3375 -0.1821 0.2479 9.5053 0.8373 12.0000 12.0000 10.8742 0.1794 0.2851 0.0959 11.3610 0.0803 0.0517 0.3234 -0.1876 0.2408 9.7281 0.7839 12.0000 12.0000 10.8344 0.1499 0.2734 0.0967 11.1073 0.0758 0.0455 0.3098 -0.1937 0.2335 9.7893 0.7652 12.0000 12.0000 10.8167 0.1373 0.2693 0.0969 11.0396 0.0741 0.0435 0.3049 -0.1980 0.2306 9.8410 0.7434 12.0000 12.0000 10.7795 0.1207 0.2646 0.0971 10.9829 0.0722 0.0411 0.2989 -0.2050 0.2268 9.8928 0.7154 12.0000 12.0000 10.7195 0.0979 0.2588 0.0973 10.9268 0.0696 0.0381 0.2911 -0.2156 0.2217 9.9446 0.6805 12.0000 12.0000 10.6351 0.0680 0.2516 0.0975 10.8713 0.0663 0.0345 0.2813 -0.2301 0.2153 9.9963 0.6369 12.0000 12.0000 10.5211 0.0295 0.2428 0.0977 10.8163 0.0622 0.0303 0.2694 -0.2496 0.2075 10.0481 0.5819 12.0000 12.0000 10.0884 -0.0204 0.2319 0.0979 10.7619 0.0570 0.0253 0.2549 -0.2754 0.1980 10.0999 0.5096 12.0000 12.0000 9.4913 -0.0874 0.2178 0.0981 10.7080 0.0500 0.0195 0.2366 -0.3108 0.1864 10.1516 0.4026 12.0000 12.0000 8.8246 -0.1888 0.1974 0.0984 10.6547 0.0396 0.0122 0.2110 -0.3655 0.1710 10.2034 0.2136 12.0000 12.0000 8.2514 -0.3710 0.1620 0.0986 10.6019 0.0211 0.0034 0.1686 -0.4651 0.1469 10.2500 0.0336 12.0000 12.0061 12.0060 -0.5448 0.1287 0.0988 10.5600 0.0033 0.0000 0.1287 0.0000 0.0000 RADIUS: 10.27 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.73 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.297177 TOTAL WEIGHT (Kg) = 0.134774 TOTAL VOLUME (IN**3) = 4.841396 TOTAL PROJECTED AREA (IN**2) = 27.8353 MOMENT OF INERTIA (SNAIL-IN**2) = 0.015294 MOMENT OF INERTIA (Kg-M**2) = 0.001727 STATIC MOMENT, ONE SIDE (IN-LB) = 0.547585 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 = 88.900 INNER LIMIT (NORMALIZED BY RADIUS) = 0.061 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5958.12 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.73, 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