20.5x14E (205x14E.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 2.7176 0.0000 0.0000 0.6250 0.0000 0.4000 0.0000 0.5000 0.0000 0.2300 0.0000 0.0000 0.2665 1.1752 4.9119 0.0410 -0.7373 0.6155 0.0211 0.3980 1.4039 0.4678 0.5048 0.2451 0.0272 -0.0105 0.5330 1.1155 6.8692 0.3208 -1.3107 0.6128 0.0776 0.3922 5.4712 0.4375 0.4847 0.2848 0.0591 0.0133 0.7995 1.0809 8.5894 1.0443 -1.3731 0.6160 0.1601 0.3824 11.7434 0.4133 0.4575 0.3423 0.0928 0.0509 1.0660 1.0807 10.0726 2.3456 -0.6560 0.6239 0.2595 0.3686 19.3005 0.3984 0.4271 0.4111 0.1259 0.0989 1.3325 1.1177 11.3187 4.2446 0.9656 0.6357 0.3668 0.3510 26.8841 0.3923 0.3964 0.4851 0.1565 0.1538 1.5990 1.1860 12.3277 6.6134 3.4149 0.6501 0.4727 0.3294 33.3551 0.3907 0.3671 0.5583 0.1826 0.2116 1.8655 1.2734 13.0996 9.1729 6.2742 0.6661 0.5681 0.3039 38.0461 0.3870 0.3401 0.6248 0.2026 0.2678 2.1320 1.3656 13.6344 11.5323 8.9753 0.6828 0.6441 0.2745 40.7249 0.3749 0.3156 0.6783 0.2148 0.3167 2.3985 1.4500 13.9322 13.2647 11.0843 0.6990 0.6915 0.2412 41.3540 0.3498 0.2937 0.7121 0.2167 0.3514 2.6650 1.5182 14.0000 13.9936 12.2407 0.7137 0.7011 0.2047 39.8856 0.3108 0.2739 0.7173 0.2045 0.3634 2.9298 1.5697 14.0000 14.0000 12.5517 0.7251 0.6832 0.1824 37.2533 0.2863 0.2640 0.7014 0.1818 0.3570 3.1662 1.6056 14.0000 14.0000 12.5949 0.7317 0.6648 0.1761 35.1355 0.2828 0.2698 0.6871 0.1621 0.3499 3.4009 1.6321 14.0000 14.0000 12.6259 0.7350 0.6460 0.1708 33.2318 0.2788 0.2749 0.6728 0.1422 0.3420 3.6356 1.6502 14.0000 14.0000 12.6587 0.7351 0.6271 0.1657 31.5033 0.2735 0.2782 0.6585 0.1220 0.3337 3.8703 1.6602 14.0000 14.0000 12.6937 0.7322 0.6084 0.1608 29.9297 0.2670 0.2794 0.6441 0.1018 0.3254 4.1049 1.6626 14.0000 14.0000 12.7303 0.7266 0.5901 0.1561 28.4931 0.2595 0.2785 0.6298 0.0821 0.3174 4.3396 1.6579 14.0000 14.0000 12.7671 0.7182 0.5723 0.1516 27.1780 0.2513 0.2753 0.6155 0.0632 0.3101 4.5743 1.6465 14.0000 14.0000 12.8026 0.7073 0.5550 0.1472 25.9709 0.2424 0.2698 0.6012 0.0454 0.3037 4.8090 1.6288 14.0000 14.0000 12.8348 0.6940 0.5384 0.1431 24.8598 0.2330 0.2619 0.5869 0.0291 0.2983 5.0437 1.6053 14.0000 14.0000 12.8657 0.6784 0.5223 0.1391 23.8345 0.2233 0.2520 0.5727 0.0143 0.2940 5.2784 1.5764 14.0000 14.0000 12.8962 0.6607 0.5069 0.1353 22.8861 0.2133 0.2401 0.5585 0.0013 0.2908 5.5131 1.5427 14.0000 14.0000 12.9332 0.6411 0.4922 0.1317 22.0066 0.2032 0.2266 0.5443 -0.0101 0.2889 5.7478 1.5044 14.0000 14.0000 12.9943 0.6196 0.4781 0.1283 21.1892 0.1931 0.2117 0.5301 -0.0197 0.2879 5.9825 1.4622 14.0000 14.0000 13.0789 0.5964 0.4644 0.1251 20.4278 0.1830 0.1963 0.5159 -0.0283 0.2874 6.2172 1.4164 14.0000 14.0000 13.1645 0.5718 0.4509 0.1221 19.7172 0.1730 0.1809 0.5017 -0.0364 0.2865 6.4518 1.3675 14.0000 14.0000 13.1910 0.5457 0.4377 0.1193 19.0525 0.1631 0.1657 0.4875 -0.0441 0.2853 6.6865 1.3159 14.0000 14.0000 13.1935 0.5184 0.4246 0.1167 18.4297 0.1535 0.1510 0.4732 -0.0516 0.2838 6.9212 1.2621 14.0000 14.0000 13.1947 0.4899 0.4117 0.1142 17.8451 0.1442 0.1368 0.4590 -0.0588 0.2818 7.1559 1.2066 14.0000 14.0000 13.1958 0.4606 0.3989 0.1120 17.2953 0.1351 0.1233 0.4447 -0.0660 0.2794 7.3906 1.1497 14.0000 14.0000 13.1956 0.4304 0.3863 0.1099 16.7774 0.1263 0.1105 0.4304 -0.0731 0.2766 7.6253 1.0919 14.0000 14.0000 13.1951 0.3995 0.3737 0.1080 16.2888 0.1179 0.0985 0.4162 -0.0802 0.2733 7.8600 1.0338 14.0000 14.0000 13.1940 0.3681 0.3613 0.1063 15.8271 0.1099 0.0874 0.4019 -0.0875 0.2695 8.0947 0.9756 14.0000 14.0000 13.1919 0.3363 0.3488 0.1048 15.3903 0.1023 0.0771 0.3877 -0.0949 0.2653 8.3294 0.9180 14.0000 14.0000 13.1895 0.3043 0.3364 0.1035 14.9764 0.0950 0.0677 0.3734 -0.1026 0.2605 8.5641 0.8612 14.0000 14.0000 13.1862 0.2722 0.3241 0.1024 14.5837 0.0882 0.0592 0.3591 -0.1105 0.2552 8.7987 0.8059 14.0000 14.0000 13.1820 0.2401 0.3117 0.1015 14.2107 0.0818 0.0516 0.3449 -0.1189 0.2494 9.0334 0.7523 14.0000 14.0000 13.1771 0.2083 0.2992 0.1007 13.8559 0.0758 0.0448 0.3306 -0.1277 0.2430 9.2681 0.7011 14.0000 14.0000 13.1711 0.1768 0.2867 0.1002 13.5181 0.0702 0.0388 0.3164 -0.1370 0.2360 9.5028 0.6525 14.0000 14.0000 13.1628 0.1457 0.2742 0.0998 13.1960 0.0651 0.0336 0.3021 -0.1469 0.2285 9.7280 0.6089 14.0000 14.0000 13.1529 0.1165 0.2620 0.0997 12.9009 0.0607 0.0292 0.2884 -0.1570 0.2207 9.7893 0.5976 13.9870 13.9870 13.1307 0.1087 0.2587 0.0997 12.8114 0.0596 0.0281 0.2846 -0.1599 0.2184 9.8410 0.5882 13.9304 13.9304 13.0441 0.1021 0.2558 0.0996 12.6962 0.0586 0.0273 0.2811 -0.1624 0.2163 9.8928 0.5754 13.8287 13.8287 12.8878 0.0920 0.2521 0.0997 12.5426 0.0573 0.0261 0.2764 -0.1668 0.2133 9.9446 0.5554 13.6820 13.6820 12.6599 0.0747 0.2467 0.0997 12.3511 0.0554 0.0243 0.2696 -0.1753 0.2090 9.9963 0.5271 13.4903 13.4903 12.3703 0.0492 0.2396 0.0997 12.1220 0.0525 0.0219 0.2605 -0.1883 0.2034 10.0481 0.4885 13.2535 13.2535 11.8744 0.0134 0.2306 0.0997 11.8557 0.0487 0.0189 0.2490 -0.2071 0.1964 10.0999 0.4357 12.9717 12.9717 11.0883 -0.0366 0.2188 0.0998 11.5527 0.0435 0.0150 0.2344 -0.2337 0.1877 10.1516 0.3578 12.6449 12.6449 10.2731 -0.1114 0.2027 0.0998 11.2132 0.0357 0.0102 0.2146 -0.2740 0.1765 10.2034 0.2038 12.2731 12.2731 10.0527 -0.2613 0.1732 0.0999 10.8375 0.0204 0.0034 0.1794 -0.3554 0.1575 10.2500 0.0261 11.9000 11.9493 11.9492 -0.4352 0.1411 0.1000 10.5112 0.0026 0.0000 0.1411 0.0000 0.0000 RADIUS: 10.25 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.280290 TOTAL WEIGHT (Kg) = 0.127116 TOTAL VOLUME (IN**3) = 4.566288 TOTAL PROJECTED AREA (IN**2) = 22.8842 MOMENT OF INERTIA (SNAIL-IN**2) = 0.012397 MOMENT OF INERTIA (Kg-M**2) = 0.001400 STATIC MOMENT, ONE SIDE (IN-LB) = 0.469199 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 = 71.531 INNER LIMIT (NORMALIZED BY RADIUS) = 0.061 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7574.57 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.66, 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