12x13N (12x13N.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 1.0000 0.8125 0.0000 0.0000 0.5000 0.0000 0.4443 0.0000 0.4443 0.0000 0.0300 0.0000 0.0000 0.1550 0.9498 2.2769 0.0212 -0.8603 0.4929 0.0076 0.4203 1.2446 0.3992 0.3726 0.0386 0.0109 -0.1794 0.3100 0.8966 3.6476 0.1665 -1.6822 0.4873 0.0281 0.3973 4.8865 0.3562 0.3672 0.0619 0.0336 -0.1705 0.4650 0.8489 4.9246 0.5530 -2.2675 0.4831 0.0582 0.3754 10.7174 0.3186 0.3555 0.0960 0.0584 -0.1539 0.6200 0.8161 6.1079 1.2872 -2.4044 0.4806 0.0946 0.3544 18.2849 0.2892 0.3371 0.1372 0.0845 -0.1315 0.7750 0.8046 7.1975 2.4525 -1.9177 0.4797 0.1342 0.3345 26.7319 0.2691 0.3143 0.1820 0.1107 -0.1061 0.9300 0.8149 8.1934 4.0799 -0.7020 0.4806 0.1740 0.3155 34.9233 0.2571 0.2897 0.2265 0.1362 -0.0801 1.0850 0.8408 9.0957 6.1033 1.2105 0.4833 0.2108 0.2976 41.8371 0.2502 0.2655 0.2669 0.1596 -0.0557 1.2400 0.8718 9.9042 8.3072 3.5636 0.4879 0.2414 0.2807 46.8361 0.2447 0.2433 0.2995 0.1798 -0.0349 1.3950 0.8964 10.6190 10.3010 5.8194 0.4945 0.2629 0.2649 49.6057 0.2374 0.2245 0.3206 0.1958 -0.0192 1.5500 0.9050 11.2401 11.5661 7.2047 0.5031 0.2720 0.2500 49.9019 0.2262 0.2094 0.3264 0.2068 -0.0102 1.7041 0.9025 11.7648 12.1261 7.7965 0.5133 0.2718 0.2362 48.5560 0.2132 0.1934 0.3204 0.2149 -0.0063 1.8428 0.9025 12.1577 12.5420 8.4909 0.5231 0.2703 0.2247 47.2878 0.2028 0.1742 0.3124 0.2221 -0.0041 1.9805 0.9044 12.4738 12.8777 9.2574 0.5331 0.2676 0.2141 45.9813 0.1936 0.1539 0.3033 0.2286 -0.0026 2.1183 0.9078 12.7159 13.1362 9.9901 0.5434 0.2639 0.2042 44.6245 0.1854 0.1359 0.2943 0.2340 -0.0013 2.2560 0.9123 12.8839 13.3178 10.5989 0.5536 0.2592 0.1952 43.2140 0.1781 0.1228 0.2860 0.2379 0.0001 2.3938 0.9177 12.9780 13.4230 11.0620 0.5636 0.2535 0.1870 41.7473 0.1716 0.1155 0.2788 0.2399 0.0019 2.5316 0.9235 13.0000 13.4542 11.3815 0.5731 0.2468 0.1795 40.2261 0.1658 0.1123 0.2722 0.2405 0.0043 2.6693 0.9294 13.0000 13.4625 11.6824 0.5821 0.2393 0.1729 38.7537 0.1607 0.1098 0.2654 0.2404 0.0060 2.8071 0.9351 13.0000 13.4709 11.9912 0.5903 0.2310 0.1671 37.3715 0.1562 0.1077 0.2581 0.2397 0.0069 2.9448 0.9401 13.0000 13.4797 12.2896 0.5974 0.2220 0.1621 36.0741 0.1524 0.1059 0.2504 0.2386 0.0068 3.0826 0.9442 13.0000 13.4896 12.5621 0.6034 0.2121 0.1579 34.8561 0.1491 0.1043 0.2420 0.2371 0.0056 3.2203 0.9470 13.0000 13.5007 12.7879 0.6080 0.2014 0.1545 33.7123 0.1463 0.1028 0.2327 0.2353 0.0033 3.3581 0.9481 13.0000 13.5134 12.9424 0.6111 0.1899 0.1518 32.6379 0.1440 0.1015 0.2224 0.2335 -0.0005 3.4959 0.9472 13.0000 13.5282 13.0008 0.6123 0.1775 0.1500 31.6286 0.1421 0.1001 0.2107 0.2318 -0.0059 3.6336 0.9439 13.0000 13.5436 13.0008 0.6116 0.1644 0.1487 30.6773 0.1403 0.0984 0.1979 0.2297 -0.0125 3.7714 0.9379 13.0000 13.5581 13.0007 0.6088 0.1506 0.1473 29.7766 0.1381 0.0962 0.1843 0.2269 -0.0195 3.9091 0.9288 13.0000 13.5715 13.0007 0.6036 0.1362 0.1459 28.9226 0.1355 0.0934 0.1700 0.2232 -0.0270 4.0469 0.9161 13.0000 13.5837 13.0007 0.5958 0.1211 0.1445 28.1118 0.1324 0.0900 0.1548 0.2185 -0.0350 4.1847 0.8997 13.0000 13.5944 13.0006 0.5853 0.1053 0.1432 27.3406 0.1288 0.0860 0.1387 0.2129 -0.0434 4.3224 0.8790 13.0000 13.6035 13.0006 0.5719 0.0887 0.1418 26.6059 0.1246 0.0813 0.1216 0.2063 -0.0524 4.4602 0.8538 13.0000 13.6106 13.0005 0.5554 0.0713 0.1404 25.9047 0.1199 0.0760 0.1034 0.1986 -0.0620 4.5979 0.8236 13.0000 13.6153 13.0005 0.5355 0.0530 0.1390 25.2339 0.1145 0.0701 0.0841 0.1898 -0.0721 4.7357 0.7880 13.0000 13.6171 13.0004 0.5121 0.0336 0.1376 24.5907 0.1085 0.0636 0.0636 0.1799 -0.0829 4.8734 0.7468 13.0000 13.6153 13.0004 0.4851 0.0133 0.1363 23.9719 0.1018 0.0566 0.0418 0.1688 -0.0943 5.0112 0.6996 12.9998 13.6084 13.0001 0.4541 -0.0083 0.1349 23.3740 0.0944 0.0493 0.0185 0.1564 -0.1066 5.1490 0.6459 12.9567 13.5519 12.9570 0.4190 -0.0311 0.1335 22.7284 0.0862 0.0417 -0.0062 0.1427 -0.1195 5.2867 0.5854 12.8397 13.4119 12.8399 0.3797 -0.0553 0.1321 21.9869 0.0774 0.0340 -0.0326 0.1276 -0.1329 5.4245 0.5178 12.6486 13.1838 12.6488 0.3358 -0.0811 0.1308 21.1471 0.0677 0.0265 -0.0607 0.1110 -0.1473 5.5622 0.4427 12.3836 12.8590 12.3837 0.2873 -0.1084 0.1294 20.2005 0.0573 0.0193 -0.0907 0.0931 -0.1627 5.6944 0.3631 12.0597 12.4395 12.0598 0.2362 -0.1362 0.1281 19.1714 0.0465 0.0130 -0.1214 0.0747 -0.1789 5.7303 0.3402 11.9600 12.3031 11.9601 0.2215 -0.1440 0.1277 18.8658 0.0434 0.0114 -0.1301 0.0695 -0.1835 5.7606 0.3205 11.8719 12.1788 11.8720 0.2089 -0.1507 0.1274 18.5970 0.0408 0.0102 -0.1375 0.0651 -0.1875 5.7909 0.3003 11.7802 12.0451 11.7803 0.1960 -0.1574 0.1271 18.3167 0.0382 0.0090 -0.1450 0.0606 -0.1916 5.8212 0.2797 11.6849 11.9003 11.6850 0.1828 -0.1643 0.1268 18.0229 0.0355 0.0078 -0.1527 0.0560 -0.1958 5.8515 0.2587 11.5861 11.7426 11.5861 0.1694 -0.1712 0.1265 17.7128 0.0327 0.0067 -0.1604 0.0514 -0.2001 5.8818 0.2373 11.4837 11.5692 11.4837 0.1557 -0.1782 0.1262 17.3827 0.0299 0.0057 -0.1683 0.0467 -0.2045 5.9121 0.2122 11.3777 11.3760 11.3777 0.1387 -0.1863 0.1259 17.0269 0.0267 0.0046 -0.1774 0.0404 -0.2096 5.9424 0.1762 11.2681 11.1567 11.3360 0.1113 -0.1974 0.1256 16.6365 0.0221 0.0032 -0.1899 0.0288 -0.2166 5.9727 0.1162 11.1549 10.9008 11.7022 0.0611 -0.2150 0.1253 16.1971 0.0146 0.0014 -0.2100 0.0051 -0.2278 6.0000 0.0075 11.0500 11.0500 11.0499 -0.0369 -0.2448 0.1250 16.3364 0.0009 0.0000 -0.2448 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.55 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.106574 TOTAL WEIGHT (Kg) = 0.048333 TOTAL VOLUME (IN**3) = 1.736221 TOTAL PROJECTED AREA (IN**2) = 8.1855 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001478 MOMENT OF INERTIA (Kg-M**2) = 0.000167 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095953 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 = 83.999 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13317.44 BASED ON MODULUS (MILLION) = 1.60 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.