14x13M (14x13M.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 1.2480 -3.9784 0.0000 0.0000 0.6240 0.0000 0.2841 0.0000 0.3545 0.0000 0.1600 0.0000 0.0000 0.1200 1.2079 -2.5641 0.0145 -0.5412 0.6181 0.0083 0.2771 1.1029 0.3347 0.6211 0.1658 0.0093 -0.1292 0.2400 1.1635 -1.2114 0.1123 -1.0375 0.6127 0.0309 0.2703 4.2595 0.3144 0.6146 0.1814 0.0279 -0.1263 0.3600 1.1228 0.0798 0.3660 -1.3949 0.6079 0.0639 0.2636 9.1902 0.2960 0.5981 0.2029 0.0512 -0.1228 0.4800 1.0944 1.3096 0.8358 -1.5243 0.6040 0.1039 0.2571 15.4901 0.2813 0.5714 0.2287 0.0777 -0.1187 0.6000 1.0845 2.4779 1.5649 -1.3580 0.6011 0.1474 0.2507 22.5431 0.2719 0.5383 0.2573 0.1056 -0.1138 0.7200 1.0943 3.5847 2.5677 -0.8590 0.5995 0.1911 0.2445 29.5786 0.2676 0.5025 0.2870 0.1332 -0.1078 0.8400 1.1199 4.6300 3.8149 -0.0389 0.5993 0.2313 0.2385 35.8599 0.2670 0.4672 0.3151 0.1592 -0.1010 0.9600 1.1524 5.6138 5.2152 1.0193 0.6007 0.2649 0.2326 40.8471 0.2680 0.4349 0.3388 0.1819 -0.0941 1.0800 1.1812 6.5361 6.6016 2.1428 0.6040 0.2883 0.2268 44.2117 0.2680 0.4079 0.3548 0.2000 -0.0882 1.2000 1.1961 7.3969 7.7335 3.0659 0.6092 0.2981 0.2213 45.7266 0.2647 0.3881 0.3599 0.2120 -0.0848 1.3233 1.1994 8.2175 8.5880 3.7605 0.6161 0.2980 0.2157 45.9264 0.2587 0.3729 0.3569 0.2192 -0.0832 1.5038 1.2057 9.3013 9.7144 4.8120 0.6268 0.2964 0.2079 45.7945 0.2506 0.3525 0.3517 0.2271 -0.0801 1.6876 1.2138 10.2622 10.7140 5.8974 0.6383 0.2933 0.2002 45.2973 0.2430 0.3333 0.3456 0.2331 -0.0767 1.8714 1.2232 11.0788 11.5647 6.9620 0.6500 0.2890 0.1930 44.5247 0.2360 0.3154 0.3389 0.2372 -0.0732 2.0552 1.2335 11.7511 12.2664 7.9736 0.6619 0.2835 0.1861 43.5288 0.2295 0.2986 0.3315 0.2397 -0.0698 2.2390 1.2442 12.2792 12.8190 8.9032 0.6736 0.2770 0.1795 42.3406 0.2234 0.2826 0.3233 0.2407 -0.0663 2.4228 1.2551 12.6631 13.2228 9.7248 0.6850 0.2694 0.1734 40.9786 0.2176 0.2675 0.3145 0.2402 -0.0628 2.6066 1.2658 12.9027 13.4782 10.4155 0.6958 0.2608 0.1676 39.4535 0.2121 0.2530 0.3051 0.2384 -0.0590 2.7903 1.2759 12.9981 13.5857 10.9558 0.7057 0.2512 0.1622 37.7720 0.2069 0.2393 0.2949 0.2352 -0.0550 2.9741 1.2850 13.0000 13.5973 11.3735 0.7146 0.2406 0.1571 36.0407 0.2019 0.2264 0.2841 0.2312 -0.0512 3.1579 1.2929 13.0000 13.6066 11.7421 0.7222 0.2294 0.1524 34.4404 0.1970 0.2144 0.2726 0.2273 -0.0490 3.3417 1.2991 13.0000 13.6158 12.0633 0.7283 0.2174 0.1481 32.9623 0.1924 0.2035 0.2604 0.2234 -0.0482 3.5255 1.3034 13.0000 13.6251 12.3372 0.7326 0.2048 0.1441 31.5951 0.1878 0.1935 0.2476 0.2194 -0.0488 3.7093 1.3054 13.0000 13.6347 12.5639 0.7349 0.1915 0.1405 30.3285 0.1834 0.1845 0.2341 0.2150 -0.0508 3.8931 1.3048 13.0000 13.6447 12.7432 0.7350 0.1776 0.1373 29.1534 0.1792 0.1764 0.2199 0.2102 -0.0539 4.0769 1.3013 13.0000 13.6554 12.8753 0.7327 0.1629 0.1344 28.0614 0.1750 0.1691 0.2050 0.2048 -0.0582 4.2607 1.2946 13.0000 13.6670 12.9603 0.7277 0.1475 0.1320 27.0452 0.1708 0.1626 0.1895 0.1987 -0.0636 4.4445 1.2842 13.0000 13.6795 12.9980 0.7198 0.1315 0.1298 26.0983 0.1667 0.1567 0.1733 0.1918 -0.0699 4.6283 1.2699 13.0000 13.6933 13.0001 0.7087 0.1147 0.1281 25.2147 0.1627 0.1511 0.1564 0.1838 -0.0771 4.8121 1.2513 13.0000 13.7083 13.0002 0.6942 0.0972 0.1267 24.3891 0.1585 0.1451 0.1387 0.1746 -0.0849 4.9959 1.2281 13.0000 13.7248 13.0002 0.6762 0.0791 0.1257 23.6167 0.1543 0.1386 0.1205 0.1639 -0.0933 5.1797 1.2000 13.0000 13.7430 13.0002 0.6543 0.0603 0.1250 22.8934 0.1500 0.1317 0.1015 0.1517 -0.1021 5.3634 1.1666 13.0000 13.7616 13.0002 0.6284 0.0410 0.1245 22.2132 0.1453 0.1240 0.0819 0.1380 -0.1113 5.5472 1.1275 13.0000 13.7795 13.0001 0.5981 0.0213 0.1240 21.5711 0.1399 0.1154 0.0615 0.1225 -0.1209 5.7310 1.0824 13.0000 13.7965 13.0001 0.5633 0.0012 0.1236 20.9637 0.1337 0.1059 0.0405 0.1052 -0.1308 5.9148 1.0311 13.0000 13.8123 13.0001 0.5238 -0.0193 0.1231 20.3880 0.1269 0.0958 0.0188 0.0861 -0.1409 6.0986 0.9731 13.0000 13.8267 13.0001 0.4792 -0.0402 0.1226 19.8411 0.1193 0.0850 -0.0036 0.0649 -0.1512 6.2824 0.9081 13.0000 13.8391 13.0001 0.4295 -0.0613 0.1221 19.3202 0.1109 0.0738 -0.0267 0.0417 -0.1618 6.4662 0.8352 13.0000 13.8489 13.0003 0.3737 -0.0830 0.1216 18.8226 0.1016 0.0622 -0.0507 0.0160 -0.1726 6.6423 0.7501 12.9543 14.0504 12.8965 0.3061 -0.1028 0.1211 18.6064 0.0909 0.0499 -0.0753 -0.0157 -0.1846 6.6854 0.7264 12.9257 14.2036 12.8383 0.2865 -0.1067 0.1210 18.6824 0.0879 0.0467 -0.0811 -0.0250 -0.1878 6.7207 0.7051 12.8969 14.3672 12.7867 0.2685 -0.1098 0.1209 18.7901 0.0853 0.0438 -0.0861 -0.0337 -0.1906 6.7561 0.6812 12.8636 14.5676 12.7341 0.2481 -0.1134 0.1208 18.9409 0.0823 0.0408 -0.0917 -0.0436 -0.1938 6.7914 0.6536 12.8255 14.8072 12.6901 0.2240 -0.1177 0.1207 19.1369 0.0789 0.0374 -0.0982 -0.0556 -0.1977 6.8268 0.6207 12.7827 15.0882 12.6557 0.1950 -0.1234 0.1206 19.3797 0.0749 0.0335 -0.1062 -0.0703 -0.2024 6.8621 0.5789 12.7353 15.4132 12.6364 0.1591 -0.1314 0.1205 19.6711 0.0698 0.0290 -0.1166 -0.0880 -0.2084 6.8975 0.5211 12.6832 15.7846 12.6457 0.1143 -0.1431 0.1205 20.0126 0.0628 0.0234 -0.1309 -0.1079 -0.2157 6.9328 0.4413 12.6265 16.2032 12.7064 0.0573 -0.1604 0.1204 20.4038 0.0531 0.0167 -0.1511 -0.1308 -0.2251 6.9682 0.3249 12.5650 16.6691 12.9025 -0.0210 -0.1880 0.1203 20.8431 0.0391 0.0090 -0.1819 -0.1597 -0.2383 7.0000 0.0519 12.5057 12.5057 12.5057 -0.1755 -0.2572 0.1202 15.8724 0.0062 0.0000 -0.2572 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.207440 TOTAL WEIGHT (Kg) = 0.094077 TOTAL VOLUME (IN**3) = 3.379457 TOTAL PROJECTED AREA (IN**2) = 13.7721 MOMENT OF INERTIA (SNAIL-IN**2) = 0.004429 MOMENT OF INERTIA (Kg-M**2) = 0.000500 STATIC MOMENT, ONE SIDE (IN-LB) = 0.233740 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 = 112.994 INNER LIMIT (NORMALIZED BY RADIUS) = 0.089 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 15656.01 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.