14x13N (14x13N.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 1.1900 -1.7469 0.0000 0.0000 0.5950 0.0000 0.4389 0.0000 0.5223 0.0000 0.2100 0.0000 0.0000 0.1750 1.1316 0.0703 0.0192 -0.6179 0.5872 0.0102 0.4198 0.9994 0.4751 0.5169 0.2167 0.0193 -0.0512 0.3500 1.0659 1.7680 0.1510 -1.2010 0.5814 0.0376 0.4014 3.9268 0.4279 0.4977 0.2346 0.0472 -0.0427 0.5250 1.0009 3.3463 0.5025 -1.5757 0.5777 0.0775 0.3838 8.6619 0.3841 0.4663 0.2605 0.0789 -0.0265 0.7000 0.9456 4.8051 1.1759 -1.5628 0.5761 0.1256 0.3668 14.9687 0.3469 0.4260 0.2914 0.1131 -0.0049 0.8750 0.9074 6.1445 2.2588 -1.0016 0.5768 0.1776 0.3505 22.3354 0.3181 0.3812 0.3244 0.1486 0.0195 1.0500 0.8893 7.3645 3.7999 0.2247 0.5798 0.2291 0.3350 29.9406 0.2979 0.3361 0.3564 0.1839 0.0442 1.2250 0.8884 8.4650 5.7647 2.1285 0.5852 0.2759 0.3202 36.8318 0.2844 0.2939 0.3846 0.2176 0.0670 1.4000 0.8968 9.4461 7.9735 4.5282 0.5930 0.3137 0.3061 42.1906 0.2745 0.2570 0.4059 0.2479 0.0858 1.5750 0.9043 10.3078 10.0494 6.9598 0.6034 0.3382 0.2926 45.4406 0.2646 0.2270 0.4175 0.2733 0.0993 1.7500 0.9018 11.0500 11.4364 8.6741 0.6163 0.3450 0.2799 46.1258 0.2525 0.2047 0.4160 0.2927 0.1059 1.9244 0.8932 11.6707 12.0977 9.5434 0.6312 0.3394 0.2680 45.0156 0.2394 0.1884 0.4057 0.3074 0.1075 2.0879 0.8902 12.1452 12.6032 10.2673 0.6457 0.3335 0.2574 43.8515 0.2292 0.1764 0.3963 0.3195 0.1079 2.2509 0.8916 12.5142 13.0011 10.8955 0.6605 0.3273 0.2475 42.5920 0.2207 0.1670 0.3873 0.3298 0.1073 2.4138 0.8968 12.7796 13.2935 11.4208 0.6753 0.3206 0.2382 41.2351 0.2137 0.1595 0.3786 0.3384 0.1062 2.5767 0.9053 12.9414 13.4802 11.8341 0.6900 0.3135 0.2296 39.7815 0.2078 0.1537 0.3699 0.3452 0.1046 2.7397 0.9163 12.9998 13.5611 12.1280 0.7042 0.3058 0.2215 38.2312 0.2030 0.1492 0.3613 0.3503 0.1027 2.9026 0.9293 13.0000 13.5819 12.3394 0.7177 0.2977 0.2141 36.6760 0.1989 0.1458 0.3527 0.3539 0.1004 3.0655 0.9437 13.0000 13.6015 12.5212 0.7303 0.2892 0.2072 35.2281 0.1956 0.1433 0.3438 0.3564 0.0972 3.2284 0.9589 13.0000 13.6203 12.6738 0.7416 0.2803 0.2010 33.8793 0.1928 0.1416 0.3348 0.3577 0.0931 3.3914 0.9742 13.0000 13.6387 12.7972 0.7514 0.2709 0.1954 32.6215 0.1904 0.1405 0.3253 0.3578 0.0882 3.5543 0.9892 13.0000 13.6573 12.8914 0.7595 0.2609 0.1905 31.4477 0.1884 0.1399 0.3154 0.3566 0.0826 3.7172 1.0032 13.0000 13.6762 12.9564 0.7656 0.2502 0.1861 30.3511 0.1867 0.1396 0.3050 0.3541 0.0762 3.8802 1.0156 13.0000 13.6958 12.9923 0.7694 0.2388 0.1823 29.3258 0.1852 0.1396 0.2940 0.3503 0.0691 4.0431 1.0258 13.0000 13.7163 13.0000 0.7707 0.2265 0.1792 28.3662 0.1838 0.1398 0.2821 0.3452 0.0612 4.2060 1.0332 13.0000 13.7360 13.0004 0.7692 0.2135 0.1762 27.4638 0.1821 0.1393 0.2694 0.3386 0.0529 4.3690 1.0373 13.0000 13.7539 13.0007 0.7646 0.1998 0.1732 26.6125 0.1797 0.1378 0.2558 0.3306 0.0440 4.5319 1.0373 13.0000 13.7701 13.0009 0.7568 0.1854 0.1702 25.8079 0.1766 0.1354 0.2412 0.3210 0.0347 4.6948 1.0327 13.0000 13.7842 13.0008 0.7454 0.1703 0.1672 25.0459 0.1727 0.1318 0.2254 0.3100 0.0250 4.8578 1.0229 13.0000 13.7961 13.0007 0.7302 0.1542 0.1643 24.3230 0.1680 0.1270 0.2085 0.2975 0.0147 5.0207 1.0073 13.0000 13.8056 13.0007 0.7109 0.1372 0.1613 23.6358 0.1624 0.1209 0.1902 0.2834 0.0040 5.1836 0.9852 13.0000 13.8123 13.0006 0.6872 0.1192 0.1583 22.9811 0.1559 0.1136 0.1705 0.2679 -0.0074 5.3466 0.9561 13.0000 13.8159 13.0005 0.6590 0.1000 0.1553 22.3559 0.1485 0.1050 0.1493 0.2508 -0.0194 5.5095 0.9193 13.0000 13.8158 13.0004 0.6259 0.0797 0.1523 21.7571 0.1400 0.0953 0.1265 0.2323 -0.0321 5.6724 0.8743 13.0000 13.8112 13.0004 0.5877 0.0581 0.1493 21.1819 0.1306 0.0846 0.1020 0.2122 -0.0456 5.8353 0.8204 13.0000 13.8009 13.0003 0.5442 0.0351 0.1463 20.6268 0.1201 0.0731 0.0757 0.1906 -0.0598 5.9983 0.7570 13.0000 13.7830 13.0003 0.4950 0.0107 0.1434 20.0880 0.1085 0.0611 0.0475 0.1675 -0.0749 6.1612 0.6836 12.9493 13.7034 12.9495 0.4399 -0.0154 0.1404 19.4931 0.0960 0.0490 0.0174 0.1428 -0.0908 6.3241 0.5994 12.7951 13.5037 12.7953 0.3787 -0.0433 0.1374 18.7697 0.0823 0.0371 -0.0148 0.1164 -0.1073 6.4871 0.5040 12.5374 13.1728 12.5375 0.3111 -0.0730 0.1344 17.9100 0.0677 0.0258 -0.0493 0.0886 -0.1247 6.6433 0.4012 12.1929 12.7086 12.1930 0.2399 -0.1033 0.1315 16.9334 0.0528 0.0162 -0.0844 0.0605 -0.1427 6.6854 0.3717 12.0841 12.5529 12.0842 0.2197 -0.1117 0.1308 16.6383 0.0486 0.0139 -0.0942 0.0528 -0.1478 6.7207 0.3461 11.9871 12.4091 11.9872 0.2024 -0.1189 0.1301 16.3761 0.0450 0.0120 -0.1026 0.0462 -0.1521 6.7561 0.3200 11.8853 12.2516 11.8854 0.1847 -0.1262 0.1295 16.0989 0.0414 0.0103 -0.1111 0.0396 -0.1566 6.7914 0.2933 11.7786 12.0777 11.7787 0.1667 -0.1335 0.1288 15.8035 0.0378 0.0087 -0.1197 0.0329 -0.1611 6.8268 0.2659 11.6671 11.8835 11.6671 0.1483 -0.1410 0.1282 15.4852 0.0341 0.0071 -0.1284 0.0261 -0.1657 6.8621 0.2379 11.5506 11.6632 11.5507 0.1296 -0.1485 0.1275 15.1367 0.0303 0.0058 -0.1372 0.0194 -0.1705 6.8975 0.2093 11.4293 11.4074 11.4293 0.1106 -0.1561 0.1269 14.7468 0.0266 0.0045 -0.1462 0.0126 -0.1753 6.9328 0.1757 11.3032 11.1000 11.3029 0.0870 -0.1649 0.1262 14.2958 0.0222 0.0032 -0.1566 0.0036 -0.1809 6.9682 0.1204 11.1721 10.7108 11.5366 0.0425 -0.1787 0.1256 13.7466 0.0151 0.0015 -0.1730 -0.0163 -0.1897 7.0000 0.0062 11.0500 11.0500 11.0500 -0.0602 -0.2050 0.1250 14.1030 0.0008 0.0000 -0.2050 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.60 HUB RADIUS (IN) HUBTRA: 1.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.154512 TOTAL WEIGHT (Kg) = 0.070074 TOTAL VOLUME (IN**3) = 2.517204 TOTAL PROJECTED AREA (IN**2) = 10.7971 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003179 MOMENT OF INERTIA (Kg-M**2) = 0.000359 STATIC MOMENT, ONE SIDE (IN-LB) = 0.168511 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 = 80.475 INNER LIMIT (NORMALIZED BY RADIUS) = 0.085 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13348.20 BASED ON MODULUS (MILLION) = 2.60 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.