21x12WE (21x12WE.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 0.3480 0.0000 0.4350 0.0000 0.1750 0.0000 0.0000 0.2730 1.1801 12.0000 0.0439 -0.7234 0.6156 0.0217 0.3447 1.4671 0.4067 0.4457 0.1920 0.0239 -0.0303 0.5460 1.1374 12.0000 0.3378 -1.2401 0.6140 0.0799 0.3346 5.6229 0.3806 0.4365 0.2353 0.0484 -0.0053 0.8190 1.1292 12.0000 1.0715 -1.1746 0.6190 0.1646 0.3180 11.7620 0.3590 0.4203 0.2979 0.0710 0.0343 1.0920 1.1609 12.0000 2.3291 -0.3006 0.6292 0.2667 0.2946 18.7499 0.3420 0.4003 0.3743 0.0908 0.0850 1.3650 1.2308 12.0000 4.0644 1.4057 0.6434 0.3765 0.2664 25.3563 0.3278 0.3787 0.4585 0.1073 0.1432 1.6380 1.3295 12.0000 6.1101 3.7626 0.6604 0.4848 0.2404 30.6969 0.3196 0.3566 0.5438 0.1202 0.2051 1.9110 1.4431 12.0000 8.2131 6.3023 0.6789 0.5821 0.2173 34.3728 0.3136 0.3350 0.6227 0.1292 0.2664 2.1840 1.5571 12.0000 10.0820 8.5424 0.6976 0.6590 0.1969 36.3049 0.3066 0.3152 0.6870 0.1335 0.3213 2.4570 1.6588 12.0000 11.4285 10.1854 0.7154 0.7061 0.1790 36.5123 0.2970 0.2995 0.7277 0.1308 0.3618 2.7300 1.7391 12.0000 11.9949 10.9713 0.7310 0.7140 0.1636 34.9646 0.2845 0.2912 0.7348 0.1161 0.3776 3.0013 1.7982 12.0000 12.0000 11.1180 0.7427 0.6943 0.1504 32.4704 0.2705 0.2891 0.7185 0.0910 0.3731 3.2434 1.8393 12.0000 12.0000 11.2263 0.7494 0.6761 0.1404 30.4914 0.2583 0.2871 0.7038 0.0681 0.3676 3.4838 1.8698 12.0000 12.0000 11.3191 0.7528 0.6576 0.1320 28.7319 0.2469 0.2855 0.6891 0.0449 0.3609 3.7242 1.8906 12.0000 12.0000 11.3959 0.7529 0.6388 0.1250 27.1496 0.2364 0.2843 0.6745 0.0215 0.3530 3.9647 1.9022 12.0000 12.0000 11.4564 0.7500 0.6198 0.1193 25.7211 0.2270 0.2833 0.6598 -0.0015 0.3445 4.2051 1.9051 12.0000 12.0000 11.4989 0.7441 0.6009 0.1148 24.4266 0.2187 0.2823 0.6451 -0.0234 0.3359 4.4455 1.8997 12.0000 12.0000 11.5204 0.7356 0.5820 0.1114 23.2492 0.2116 0.2811 0.6305 -0.0437 0.3276 4.6859 1.8867 12.0000 12.0000 11.5124 0.7244 0.5636 0.1089 22.1746 0.2055 0.2790 0.6159 -0.0620 0.3201 4.9263 1.8665 12.0000 12.0000 11.4823 0.7107 0.5457 0.1074 21.1906 0.2004 0.2756 0.6013 -0.0777 0.3138 5.1667 1.8397 12.0000 12.0000 11.4481 0.6948 0.5285 0.1064 20.2866 0.1958 0.2702 0.5868 -0.0908 0.3089 5.4071 1.8067 12.0000 12.0000 11.4176 0.6767 0.5122 0.1056 19.4538 0.1907 0.2619 0.5723 -0.1014 0.3055 5.6476 1.7682 12.0000 12.0000 11.3905 0.6565 0.4967 0.1048 18.6842 0.1852 0.2507 0.5577 -0.1094 0.3035 5.8880 1.7245 12.0000 12.0000 11.3688 0.6345 0.4820 0.1040 17.9713 0.1794 0.2374 0.5431 -0.1152 0.3025 6.1284 1.6762 12.0000 12.0000 11.3482 0.6108 0.4677 0.1033 17.3092 0.1732 0.2232 0.5285 -0.1201 0.3014 6.3688 1.6238 12.0000 12.0000 11.3277 0.5855 0.4536 0.1027 16.6928 0.1668 0.2086 0.5139 -0.1246 0.2999 6.6092 1.5679 12.0000 12.0000 11.3075 0.5588 0.4397 0.1021 16.1177 0.1601 0.1937 0.4993 -0.1286 0.2980 6.8496 1.5090 12.0000 12.0000 11.2876 0.5308 0.4262 0.1016 15.5799 0.1533 0.1788 0.4847 -0.1324 0.2957 7.0900 1.4475 12.0000 12.0000 11.2680 0.5017 0.4128 0.1011 15.0761 0.1463 0.1641 0.4701 -0.1359 0.2931 7.3304 1.3840 12.0000 12.0000 11.2489 0.4716 0.3997 0.1007 14.6031 0.1393 0.1496 0.4555 -0.1393 0.2901 7.5709 1.3190 12.0000 12.0000 11.2301 0.4406 0.3867 0.1003 14.1583 0.1323 0.1356 0.4409 -0.1427 0.2866 7.8113 1.2530 12.0000 12.0000 11.2118 0.4090 0.3739 0.1000 13.7393 0.1253 0.1222 0.4263 -0.1461 0.2827 8.0517 1.1865 12.0000 12.0000 11.1940 0.3769 0.3612 0.0997 13.3439 0.1183 0.1094 0.4117 -0.1498 0.2783 8.2921 1.1201 12.0000 12.0000 11.1764 0.3443 0.3487 0.0995 12.9703 0.1115 0.0974 0.3971 -0.1537 0.2735 8.5325 1.0542 12.0000 12.0000 11.1590 0.3115 0.3362 0.0993 12.6167 0.1047 0.0863 0.3824 -0.1580 0.2682 8.7729 0.9894 12.0000 12.0000 11.1421 0.2786 0.3237 0.0992 12.2816 0.0982 0.0760 0.3678 -0.1628 0.2624 9.0133 0.9262 12.0000 12.0000 11.1255 0.2458 0.3113 0.0992 11.9636 0.0919 0.0667 0.3532 -0.1680 0.2561 9.2538 0.8652 12.0000 12.0000 11.1092 0.2131 0.2989 0.0992 11.6614 0.0858 0.0582 0.3386 -0.1740 0.2492 9.4942 0.8067 12.0000 12.0000 11.0929 0.1808 0.2865 0.0992 11.3739 0.0800 0.0507 0.3240 -0.1806 0.2418 9.7346 0.7513 12.0000 12.0000 11.0763 0.1491 0.2739 0.0993 11.1001 0.0746 0.0440 0.3094 -0.1880 0.2339 9.9652 0.7017 12.0000 12.0000 11.0597 0.1191 0.2618 0.0995 10.8493 0.0698 0.0385 0.2954 -0.1960 0.2257 10.0280 0.6888 12.0000 12.0000 11.0517 0.1111 0.2585 0.0995 10.7830 0.0685 0.0371 0.2915 -0.1983 0.2234 10.0811 0.6748 12.0000 12.0000 11.0234 0.1011 0.2551 0.0995 10.7276 0.0672 0.0356 0.2871 -0.2021 0.2205 10.1341 0.6544 12.0000 12.0000 10.9710 0.0846 0.2504 0.0996 10.6727 0.0652 0.0335 0.2809 -0.2095 0.2163 10.1871 0.6268 12.0000 12.0000 10.8977 0.0609 0.2444 0.0996 10.6184 0.0625 0.0308 0.2727 -0.2210 0.2108 10.2402 0.5907 12.0000 12.0000 10.8047 0.0286 0.2368 0.0997 10.5647 0.0589 0.0274 0.2623 -0.2372 0.2039 10.2932 0.5437 12.0000 12.0000 10.5580 -0.0145 0.2272 0.0997 10.5115 0.0542 0.0232 0.2493 -0.2595 0.1954 10.3462 0.4810 12.0000 12.0000 10.0349 -0.0734 0.2148 0.0998 10.4588 0.0480 0.0182 0.2330 -0.2905 0.1849 10.3992 0.3888 12.0000 12.0000 9.5213 -0.1614 0.1971 0.0999 10.4066 0.0388 0.0119 0.2106 -0.3375 0.1713 10.4523 0.2132 12.0000 12.0000 9.6602 -0.3317 0.1645 0.0999 10.3550 0.0213 0.0036 0.1712 -0.4298 0.1491 10.5000 0.0301 12.0000 12.0061 12.0060 -0.5098 0.1310 0.1000 10.3140 0.0030 0.0000 0.1310 0.0000 0.0000 RADIUS: 10.50 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) = 0.296096 TOTAL WEIGHT (Kg) = 0.134284 TOTAL VOLUME (IN**3) = 4.823777 TOTAL PROJECTED AREA (IN**2) = 27.1836 MOMENT OF INERTIA (SNAIL-IN**2) = 0.015320 MOMENT OF INERTIA (Kg-M**2) = 0.001730 STATIC MOMENT, ONE SIDE (IN-LB) = 0.544362 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 = 80.202 INNER LIMIT (NORMALIZED BY RADIUS) = 0.060 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5965.06 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.75, 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