15x12 (15x12.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 -2.1120 0.0000 0.0000 0.6250 0.0000 0.4896 0.0000 0.6120 0.0000 0.1200 0.0000 0.0000 0.1800 1.1930 -0.3559 0.0212 -0.9135 0.6179 0.0073 0.4596 1.0720 0.5483 0.6216 0.1268 0.0151 -0.1688 0.3600 1.1341 1.2835 0.1655 -1.7652 0.6143 0.0272 0.4309 4.1843 0.4887 0.6030 0.1449 0.0428 -0.1626 0.5400 1.0816 2.8063 0.5448 -2.3606 0.6139 0.0563 0.4036 9.1219 0.4365 0.5751 0.1714 0.0747 -0.1516 0.7200 1.0441 4.2125 1.2540 -2.5186 0.6164 0.0915 0.3776 15.4925 0.3942 0.5401 0.2031 0.1090 -0.1370 0.9000 1.0279 5.5020 2.3569 -2.0943 0.6214 0.1300 0.3529 22.6262 0.3628 0.5013 0.2373 0.1439 -0.1201 1.0800 1.0342 6.6749 3.8626 -1.0103 0.6285 0.1686 0.3296 29.6493 0.3409 0.4614 0.2711 0.1774 -0.1021 1.2600 1.0581 7.7311 5.6931 0.6951 0.6376 0.2043 0.3077 35.7206 0.3256 0.4229 0.3014 0.2078 -0.0844 1.4400 1.0906 8.6707 7.6546 2.8166 0.6482 0.2341 0.2871 40.2318 0.3131 0.3875 0.3252 0.2335 -0.0681 1.6200 1.1210 9.4937 9.4308 4.9555 0.6599 0.2551 0.2679 42.8157 0.3003 0.3561 0.3395 0.2526 -0.0548 1.8000 1.1404 10.2000 10.6231 6.5549 0.6726 0.2641 0.2500 43.2068 0.2851 0.3288 0.3414 0.2639 -0.0456 1.9799 1.1507 10.7893 11.2416 7.5431 0.6859 0.2640 0.2334 42.1033 0.2686 0.3041 0.3344 0.2697 -0.0399 2.1574 1.1612 11.2567 11.7275 8.4388 0.6995 0.2622 0.2184 40.8648 0.2536 0.2814 0.3267 0.2747 -0.0349 2.3348 1.1716 11.6105 12.0942 9.2365 0.7135 0.2589 0.2047 39.5025 0.2398 0.2604 0.3184 0.2791 -0.0303 2.5122 1.1819 11.8510 12.3428 9.9164 0.7276 0.2542 0.1923 38.0232 0.2273 0.2410 0.3095 0.2828 -0.0262 2.6897 1.1917 11.9781 12.4743 10.4612 0.7415 0.2480 0.1813 36.4325 0.2160 0.2234 0.3000 0.2858 -0.0223 2.8671 1.2006 12.0000 12.4980 10.8640 0.7550 0.2404 0.1715 34.7523 0.2059 0.2076 0.2899 0.2883 -0.0186 3.0445 1.2086 12.0000 12.4995 11.1920 0.7679 0.2317 0.1630 33.1618 0.1970 0.1939 0.2791 0.2910 -0.0164 3.2219 1.2152 12.0000 12.5020 11.4643 0.7799 0.2219 0.1559 31.6983 0.1894 0.1822 0.2677 0.2940 -0.0158 3.3993 1.2202 12.0000 12.5065 11.6808 0.7908 0.2111 0.1500 30.3511 0.1831 0.1726 0.2557 0.2972 -0.0168 3.5767 1.2234 12.0000 12.5140 11.8416 0.8004 0.1991 0.1455 29.1109 0.1780 0.1651 0.2431 0.3005 -0.0192 3.7541 1.2245 12.0000 12.5255 11.9467 0.8084 0.1859 0.1423 27.9688 0.1742 0.1597 0.2298 0.3038 -0.0231 3.9316 1.2232 12.0000 12.5417 11.9960 0.8146 0.1715 0.1403 26.9172 0.1717 0.1562 0.2159 0.3069 -0.0283 4.1090 1.2193 12.0000 12.5622 12.0000 0.8187 0.1560 0.1395 25.9467 0.1701 0.1541 0.2013 0.3097 -0.0348 4.2864 1.2124 12.0000 12.5829 12.0002 0.8206 0.1400 0.1387 25.0424 0.1682 0.1514 0.1861 0.3118 -0.0420 4.4638 1.2023 12.0000 12.6033 12.0003 0.8200 0.1236 0.1380 24.1975 0.1659 0.1480 0.1703 0.3130 -0.0497 4.6412 1.1888 12.0000 12.6231 12.0004 0.8166 0.1067 0.1372 23.4062 0.1631 0.1438 0.1538 0.3132 -0.0580 4.8186 1.1714 12.0000 12.6421 12.0004 0.8102 0.0894 0.1364 22.6634 0.1598 0.1388 0.1367 0.3123 -0.0668 4.9960 1.1500 12.0000 12.6602 12.0004 0.8007 0.0717 0.1357 21.9646 0.1560 0.1330 0.1189 0.3101 -0.0759 5.1734 1.1242 12.0000 12.6773 12.0004 0.7876 0.0536 0.1349 21.3059 0.1517 0.1264 0.1005 0.3065 -0.0855 5.3509 1.0938 12.0000 12.6931 12.0004 0.7709 0.0352 0.1342 20.6836 0.1467 0.1190 0.0815 0.3013 -0.0955 5.5283 1.0584 12.0000 12.7073 12.0003 0.7502 0.0163 0.1334 20.0942 0.1412 0.1108 0.0618 0.2945 -0.1058 5.7057 1.0178 12.0000 12.7196 12.0003 0.7254 -0.0028 0.1326 19.5347 0.1350 0.1020 0.0415 0.2859 -0.1163 5.8831 0.9717 12.0000 12.7295 12.0003 0.6961 -0.0223 0.1319 19.0021 0.1282 0.0925 0.0205 0.2754 -0.1272 6.0605 0.9198 12.0000 12.7363 12.0003 0.6622 -0.0421 0.1311 18.4934 0.1206 0.0825 -0.0011 0.2628 -0.1382 6.2379 0.8618 12.0000 12.7391 12.0002 0.6235 -0.0621 0.1304 18.0056 0.1124 0.0721 -0.0234 0.2481 -0.1495 6.4153 0.7975 12.0000 12.7366 12.0002 0.5796 -0.0825 0.1296 17.5353 0.1034 0.0615 -0.0463 0.2311 -0.1610 6.5928 0.7265 11.9845 12.7110 11.9847 0.5304 -0.1031 0.1288 17.0589 0.0936 0.0509 -0.0698 0.2117 -0.1725 6.7702 0.6485 11.8686 12.5738 11.8688 0.4757 -0.1241 0.1281 16.4670 0.0831 0.0404 -0.0940 0.1897 -0.1838 6.9476 0.5633 11.6394 12.3059 11.6395 0.4151 -0.1455 0.1273 15.7433 0.0717 0.0305 -0.1188 0.1650 -0.1949 7.1177 0.4746 11.3132 11.9155 11.3132 0.3513 -0.1663 0.1266 14.9190 0.0601 0.0217 -0.1433 0.1388 -0.2056 7.1629 0.4498 11.2091 11.7875 11.2092 0.3334 -0.1718 0.1264 14.6767 0.0569 0.0195 -0.1498 0.1314 -0.2085 7.2008 0.4287 11.1161 11.6714 11.1162 0.3181 -0.1765 0.1262 14.4650 0.0541 0.0177 -0.1554 0.1251 -0.2109 7.2386 0.4072 11.0179 11.5467 11.0180 0.3024 -0.1811 0.1261 14.2451 0.0513 0.0160 -0.1610 0.1186 -0.2133 7.2765 0.3853 10.9146 11.4129 10.9147 0.2865 -0.1858 0.1259 14.0162 0.0485 0.0144 -0.1666 0.1121 -0.2158 7.3144 0.3628 10.8062 11.2692 10.8062 0.2702 -0.1905 0.1258 13.7776 0.0456 0.0128 -0.1723 0.1053 -0.2183 7.3523 0.3349 10.6925 11.1149 10.6931 0.2485 -0.1964 0.1256 13.5285 0.0421 0.0109 -0.1795 0.0957 -0.2217 7.3902 0.2973 10.5737 10.9486 10.6053 0.2174 -0.2044 0.1254 13.2675 0.0373 0.0086 -0.1892 0.0811 -0.2265 7.4280 0.2441 10.4498 10.7680 10.6105 0.1713 -0.2156 0.1253 12.9919 0.0306 0.0059 -0.2031 0.0583 -0.2336 7.4659 0.1480 10.3206 10.5707 11.1098 0.0831 -0.2360 0.1251 12.6990 0.0185 0.0022 -0.2283 0.0130 -0.2470 7.5000 0.0124 10.2000 10.2000 10.1999 -0.0441 -0.2641 0.1250 12.2133 0.0016 0.0000 -0.2641 0.0000 0.0000 RADIUS: 7.50 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.206999 TOTAL WEIGHT (Kg) = 0.093877 TOTAL VOLUME (IN**3) = 3.372275 TOTAL PROJECTED AREA (IN**2) = 13.7877 MOMENT OF INERTIA (SNAIL-IN**2) = 0.004331 MOMENT OF INERTIA (Kg-M**2) = 0.000489 STATIC MOMENT, ONE SIDE (IN-LB) = 0.227665 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 = 84.620 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14302.06 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.