14x6 (14x6.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 1.1500 0.3750 0.0000 0.0000 0.5750 0.0000 0.4261 0.0000 0.4900 0.0000 0.1100 0.0000 0.0000 0.1500 1.1061 1.0298 0.0141 -0.6227 0.5692 0.0048 0.4249 0.8595 0.4700 0.4589 0.1166 0.0110 -0.1194 0.3000 1.0662 1.6440 0.1086 -1.1894 0.5665 0.0177 0.4215 3.2965 0.4494 0.4574 0.1344 0.0297 -0.1136 0.4500 1.0336 2.2178 0.3481 -1.5565 0.5665 0.0364 0.4158 7.0183 0.4298 0.4501 0.1600 0.0500 -0.1029 0.6000 1.0119 2.7510 0.7764 -1.5987 0.5688 0.0588 0.4079 11.6377 0.4127 0.4357 0.1903 0.0712 -0.0882 0.7500 1.0028 3.2438 1.4101 -1.2453 0.5731 0.0829 0.3976 16.6590 0.3988 0.4162 0.2223 0.0925 -0.0708 0.9000 1.0057 3.6960 2.2311 -0.4907 0.5789 0.1065 0.3851 21.5311 0.3873 0.3936 0.2528 0.1132 -0.0522 1.0500 1.0170 4.1078 3.1805 0.5917 0.5859 0.1276 0.3703 25.7385 0.3766 0.3694 0.2788 0.1324 -0.0340 1.2000 1.0312 4.4790 4.1560 1.8412 0.5937 0.1441 0.3532 28.8640 0.3643 0.3446 0.2973 0.1495 -0.0180 1.3500 1.0422 4.8098 5.0130 3.0090 0.6019 0.1541 0.3348 30.5827 0.3490 0.3202 0.3054 0.1639 -0.0060 1.5000 1.0447 5.1000 5.5732 3.7709 0.6101 0.1553 0.3173 30.5973 0.3315 0.2970 0.3001 0.1748 -0.0002 1.6512 1.0416 5.3515 5.8563 4.1247 0.6188 0.1502 0.3005 29.4439 0.3130 0.2756 0.2858 0.1834 0.0006 1.8224 1.0411 5.5868 6.1195 4.4866 0.6298 0.1438 0.2826 28.1212 0.2942 0.2547 0.2703 0.1931 0.0008 1.9948 1.0435 5.7703 6.3261 4.8073 0.6421 0.1370 0.2658 26.7808 0.2774 0.2368 0.2555 0.2026 0.0005 2.1672 1.0483 5.9003 6.4745 5.0782 0.6552 0.1296 0.2502 25.4296 0.2623 0.2214 0.2413 0.2118 -0.0003 2.3397 1.0551 5.9769 6.5656 5.2938 0.6688 0.1219 0.2359 24.0667 0.2489 0.2081 0.2278 0.2205 -0.0013 2.5121 1.0634 6.0000 6.6001 5.4497 0.6825 0.1137 0.2227 22.6926 0.2369 0.1966 0.2148 0.2288 -0.0024 2.6845 1.0727 6.0000 6.6093 5.5702 0.6962 0.1054 0.2108 21.3975 0.2262 0.1867 0.2023 0.2367 -0.0041 2.8569 1.0826 6.0000 6.6173 5.6757 0.7095 0.0970 0.2001 20.2359 0.2167 0.1783 0.1903 0.2442 -0.0066 3.0293 1.0924 6.0000 6.6248 5.7663 0.7221 0.0886 0.1907 19.1907 0.2083 0.1711 0.1786 0.2512 -0.0099 3.2017 1.1019 6.0000 6.6327 5.8421 0.7336 0.0798 0.1824 18.2476 0.2010 0.1649 0.1671 0.2575 -0.0138 3.3741 1.1104 6.0000 6.6417 5.9031 0.7439 0.0708 0.1753 17.3949 0.1947 0.1598 0.1559 0.2631 -0.0183 3.5466 1.1175 6.0000 6.6527 5.9492 0.7525 0.0614 0.1695 16.6229 0.1894 0.1556 0.1448 0.2678 -0.0234 3.7190 1.1227 6.0000 6.6665 5.9806 0.7592 0.0514 0.1649 15.9232 0.1852 0.1522 0.1338 0.2715 -0.0292 3.8914 1.1255 6.0000 6.6837 5.9972 0.7638 0.0409 0.1615 15.2889 0.1818 0.1495 0.1229 0.2741 -0.0356 4.0638 1.1254 6.0000 6.7048 6.0000 0.7658 0.0298 0.1593 14.7131 0.1793 0.1473 0.1118 0.2756 -0.0426 4.2362 1.1220 6.0000 6.7261 6.0000 0.7650 0.0187 0.1573 14.1818 0.1764 0.1445 0.1006 0.2758 -0.0496 4.4086 1.1146 6.0000 6.7464 6.0000 0.7610 0.0079 0.1553 13.6880 0.1730 0.1408 0.0893 0.2747 -0.0566 4.5810 1.1029 6.0000 6.7657 6.0000 0.7537 -0.0028 0.1532 13.2275 0.1690 0.1361 0.0776 0.2721 -0.0635 4.7534 1.0863 6.0000 6.7838 6.0000 0.7427 -0.0134 0.1512 12.7968 0.1643 0.1303 0.0657 0.2680 -0.0703 4.9259 1.0644 6.0000 6.8007 6.0000 0.7277 -0.0239 0.1492 12.3927 0.1588 0.1234 0.0533 0.2623 -0.0771 5.0983 1.0365 6.0000 6.8162 6.0000 0.7084 -0.0344 0.1472 12.0124 0.1526 0.1155 0.0405 0.2548 -0.0839 5.2707 1.0024 6.0000 6.8301 5.9999 0.6845 -0.0450 0.1452 11.6535 0.1455 0.1066 0.0271 0.2455 -0.0908 5.4431 0.9613 6.0000 6.8422 5.9999 0.6557 -0.0556 0.1432 11.3135 0.1376 0.0967 0.0132 0.2344 -0.0977 5.6155 0.9129 6.0000 6.8522 5.9999 0.6218 -0.0663 0.1412 10.9904 0.1289 0.0860 -0.0015 0.2213 -0.1047 5.7879 0.8567 6.0000 6.8596 6.0000 0.5824 -0.0772 0.1392 10.6818 0.1192 0.0748 -0.0169 0.2062 -0.1119 5.9603 0.7921 6.0000 6.8636 6.0000 0.5372 -0.0884 0.1371 10.3856 0.1086 0.0631 -0.0331 0.1889 -0.1193 6.1328 0.7186 5.9841 6.8473 5.9841 0.4859 -0.0999 0.1351 10.0761 0.0971 0.0512 -0.0501 0.1695 -0.1268 6.3052 0.6358 5.9162 6.7722 5.9162 0.4283 -0.1120 0.1331 9.7006 0.0846 0.0396 -0.0681 0.1477 -0.1345 6.4776 0.5432 5.7947 6.6333 5.7947 0.3641 -0.1245 0.1311 9.2567 0.0712 0.0285 -0.0871 0.1236 -0.1425 6.6429 0.4447 5.6281 6.4325 5.6281 0.2960 -0.1370 0.1292 8.7613 0.0574 0.0189 -0.1064 0.0982 -0.1506 6.6854 0.4178 5.5773 6.3684 5.5773 0.2774 -0.1403 0.1287 8.6210 0.0538 0.0167 -0.1115 0.0913 -0.1528 6.7207 0.3949 5.5325 6.3106 5.5325 0.2616 -0.1430 0.1283 8.4996 0.0506 0.0149 -0.1158 0.0854 -0.1546 6.7561 0.3715 5.4855 6.2482 5.4856 0.2455 -0.1458 0.1279 8.3733 0.0475 0.0132 -0.1202 0.0795 -0.1565 6.7914 0.3477 5.4363 6.1808 5.4363 0.2291 -0.1486 0.1274 8.2417 0.0443 0.0115 -0.1246 0.0734 -0.1583 6.8268 0.3234 5.3848 6.1076 5.3848 0.2124 -0.1514 0.1270 8.1037 0.0411 0.0100 -0.1290 0.0673 -0.1603 6.8621 0.2976 5.3311 6.0278 5.3313 0.1944 -0.1543 0.1266 7.9586 0.0377 0.0084 -0.1338 0.0604 -0.1623 6.8975 0.2638 5.2751 5.9410 5.2843 0.1686 -0.1583 0.1262 7.8057 0.0333 0.0066 -0.1401 0.0495 -0.1652 6.9328 0.2167 5.2169 5.8449 5.2813 0.1297 -0.1640 0.1258 7.6423 0.0273 0.0045 -0.1490 0.0313 -0.1696 6.9682 0.1366 5.1564 5.7367 5.4906 0.0583 -0.1737 0.1254 7.4648 0.0171 0.0018 -0.1643 -0.0046 -0.1773 7.0000 0.0099 5.1000 5.1000 5.0999 -0.0601 -0.1891 0.1250 6.6143 0.0012 0.0000 -0.1891 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.165532 TOTAL WEIGHT (Kg) = 0.075071 TOTAL VOLUME (IN**3) = 2.696721 TOTAL PROJECTED AREA (IN**2) = 12.9154 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003379 MOMENT OF INERTIA (Kg-M**2) = 0.000382 STATIC MOMENT, ONE SIDE (IN-LB) = 0.183605 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 = 86.069 INNER LIMIT (NORMALIZED BY RADIUS) = 0.082 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 15253.86 BASED ON MODULUS (MILLION) = 2.70 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.