10x14M-LH (10x14M-LH.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 1.2200 -0.5840 0.0000 0.0000 0.6100 0.0000 0.3260 0.0000 0.3978 0.0000 0.3000 0.0000 0.0000 0.0700 1.2314 0.0229 0.0791 -0.2076 0.6060 0.1077 0.3184 10.1941 0.3921 0.7025 0.3015 -0.0020 -0.0451 0.1400 1.2501 0.6506 0.2895 -0.2933 0.5937 0.1904 0.3109 18.2148 0.3887 0.6838 0.3049 0.0001 -0.0459 0.2100 1.2628 1.2958 0.6029 -0.2682 0.5759 0.2514 0.3036 24.5579 0.3834 0.6423 0.3080 0.0059 -0.0467 0.2800 1.2680 1.9554 0.9982 -0.1370 0.5609 0.2938 0.2965 29.5698 0.3759 0.5861 0.3140 0.0189 -0.0475 0.3500 1.2573 2.6263 1.4706 0.0923 0.5455 0.3209 0.2895 33.7712 0.3640 0.5187 0.3310 0.0378 -0.0488 0.4200 1.2282 3.3055 2.0336 0.4245 0.5305 0.3357 0.2827 37.6188 0.3472 0.4452 0.3443 0.0633 -0.0500 0.4900 1.1783 3.9897 2.7420 0.8950 0.5166 0.3415 0.2760 41.6883 0.3252 0.3690 0.3508 0.0975 -0.0494 0.5600 1.1083 4.6758 3.7306 1.6337 0.5047 0.3414 0.2695 46.6750 0.2987 0.2935 0.3525 0.1422 -0.0437 0.6300 1.0562 5.3607 4.9174 2.6739 0.4956 0.3386 0.2631 51.1666 0.2779 0.2391 0.3519 0.1776 -0.0358 0.7000 1.0394 6.0413 6.0088 3.7543 0.4900 0.3363 0.2570 53.7971 0.2671 0.2135 0.3511 0.1928 -0.0317 0.7734 1.0556 6.7469 6.7469 4.4527 0.4869 0.3355 0.2507 54.2369 0.2646 0.2108 0.3505 0.1873 -0.0355 0.9053 1.0837 7.9826 7.9826 5.6869 0.4819 0.3333 0.2398 54.5281 0.2598 0.2063 0.3484 0.1756 -0.0426 1.0406 1.1063 9.1887 9.1887 6.9766 0.4776 0.3304 0.2292 54.5672 0.2536 0.2003 0.3458 0.1643 -0.0481 1.1758 1.1258 10.3102 10.3102 8.2283 0.4736 0.3268 0.2192 54.3759 0.2468 0.1942 0.3424 0.1527 -0.0534 1.3111 1.1431 11.3245 11.3245 9.3784 0.4699 0.3226 0.2099 53.9664 0.2399 0.1891 0.3384 0.1405 -0.0587 1.4464 1.1583 12.2091 12.2091 10.3661 0.4662 0.3176 0.2011 53.3378 0.2329 0.1854 0.3337 0.1277 -0.0641 1.5817 1.1713 12.9414 12.9414 11.1553 0.4623 0.3120 0.1929 52.4790 0.2260 0.1830 0.3283 0.1140 -0.0691 1.7169 1.1821 13.4989 13.4989 11.7936 0.4578 0.3055 0.1854 51.3695 0.2191 0.1801 0.3222 0.0988 -0.0728 1.8522 1.1909 13.8589 13.8589 12.2597 0.4526 0.2982 0.1784 49.9788 0.2125 0.1766 0.3154 0.0817 -0.0746 1.9875 1.1974 13.9990 13.9990 12.5222 0.4464 0.2901 0.1721 48.2656 0.2060 0.1727 0.3080 0.0623 -0.0740 2.1228 1.2018 14.0000 14.0000 12.6438 0.4391 0.2813 0.1663 46.3878 0.1999 0.1689 0.3001 0.0415 -0.0720 2.2580 1.2040 14.0000 14.0000 12.7464 0.4303 0.2720 0.1612 44.6186 0.1941 0.1652 0.2916 0.0209 -0.0701 2.3933 1.2041 14.0000 14.0000 12.8342 0.4198 0.2620 0.1566 42.9535 0.1886 0.1614 0.2826 0.0002 -0.0685 2.5286 1.2021 14.0000 14.0000 12.9082 0.4074 0.2516 0.1527 41.3862 0.1835 0.1576 0.2731 -0.0207 -0.0673 2.6639 1.1979 14.0000 14.0000 12.9686 0.3928 0.2406 0.1493 39.9106 0.1789 0.1537 0.2630 -0.0421 -0.0664 2.7991 1.1915 14.0000 14.0000 13.0156 0.3759 0.2292 0.1466 38.5205 0.1747 0.1498 0.2524 -0.0643 -0.0660 2.9344 1.1830 14.0000 14.0000 13.0496 0.3563 0.2172 0.1444 37.2103 0.1709 0.1459 0.2412 -0.0876 -0.0661 3.0697 1.1723 14.0000 14.0000 13.0802 0.3338 0.2048 0.1424 35.9744 0.1670 0.1417 0.2295 -0.1123 -0.0667 3.2050 1.1594 14.0000 14.0000 13.1119 0.3082 0.1919 0.1405 34.8080 0.1629 0.1371 0.2172 -0.1387 -0.0678 3.3402 1.1445 14.0000 14.0000 13.1448 0.2793 0.1786 0.1385 33.7060 0.1585 0.1321 0.2043 -0.1670 -0.0696 3.4755 1.1273 14.0000 14.0000 13.1793 0.2468 0.1648 0.1365 32.6641 0.1539 0.1267 0.1909 -0.1976 -0.0719 3.6108 1.1080 14.0000 14.0000 13.2158 0.2105 0.1506 0.1345 31.6781 0.1490 0.1211 0.1769 -0.2306 -0.0748 3.7461 1.0866 14.0000 14.0000 13.2543 0.1701 0.1360 0.1325 30.7443 0.1440 0.1151 0.1624 -0.2664 -0.0784 3.8813 1.0630 14.0000 14.0000 13.2953 0.1254 0.1209 0.1305 29.8589 0.1387 0.1089 0.1473 -0.3053 -0.0825 4.0166 1.0372 14.0000 14.0000 13.3389 0.0761 0.1053 0.1285 29.0188 0.1333 0.1026 0.1317 -0.3475 -0.0873 4.1519 1.0093 14.0000 14.0000 13.3854 0.0221 0.0893 0.1265 28.2208 0.1277 0.0960 0.1155 -0.3932 -0.0928 4.2872 0.9792 14.0000 14.0000 13.4326 -0.0369 0.0728 0.1245 27.4622 0.1220 0.0893 0.0987 -0.4426 -0.0988 4.4224 0.9470 14.0000 14.0000 13.4586 -0.1012 0.0559 0.1225 26.7404 0.1161 0.0825 0.0814 -0.4956 -0.1051 4.5577 0.9046 13.9973 14.0012 13.3439 -0.1739 0.0373 0.1206 26.0549 0.1091 0.0741 0.0613 -0.5520 -0.1136 4.6872 0.8174 13.9720 14.0160 12.8232 -0.2630 0.0130 0.1191 25.4503 0.0973 0.0597 0.0328 -0.6053 -0.1248 4.7179 0.7917 13.9620 14.0198 12.6295 -0.2854 0.0071 0.1191 25.3114 0.0943 0.0559 0.0256 -0.6169 -0.1273 4.7429 0.7690 13.9528 14.0237 12.4517 -0.3043 0.0020 0.1192 25.2010 0.0916 0.0527 0.0194 -0.6263 -0.1293 4.7678 0.7435 13.9426 14.0302 12.2643 -0.3245 -0.0035 0.1194 25.0957 0.0888 0.0493 0.0128 -0.6358 -0.1315 4.7928 0.7134 13.9314 14.0424 12.0645 -0.3471 -0.0100 0.1198 24.9999 0.0855 0.0454 0.0051 -0.6457 -0.1339 4.8177 0.6758 13.9192 14.0656 11.8595 -0.3737 -0.0181 0.1203 24.9224 0.0813 0.0408 -0.0044 -0.6565 -0.1367 4.8427 0.6261 13.9060 14.1110 11.6641 -0.4069 -0.0289 0.1210 24.8798 0.0758 0.0351 -0.0168 -0.6688 -0.1402 4.8676 0.5569 13.8919 14.2035 11.5129 -0.4506 -0.0441 0.1219 24.9104 0.0679 0.0278 -0.0338 -0.6834 -0.1448 4.8926 0.4569 13.8767 14.4106 11.4997 -0.5090 -0.0653 0.1230 25.1159 0.0562 0.0188 -0.0574 -0.6998 -0.1501 4.9175 0.3079 13.8605 15.0163 12.0240 -0.5852 -0.0937 0.1243 25.9196 0.0383 0.0085 -0.0889 -0.7135 -0.1539 4.9400 0.0268 13.8451 20.4238 20.4238 -0.7098 -0.1488 0.1256 33.3451 0.0034 0.0000 -0.1488 0.0000 0.0000 RADIUS: 4.99 PROPELLER RADIUS (IN) HUBRAD: 0.61 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.115748 TOTAL WEIGHT (Kg) = 0.052493 TOTAL VOLUME (IN**3) = 1.885675 TOTAL PROJECTED AREA (IN**2) = 8.2772 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001377 MOMENT OF INERTIA (Kg-M**2) = 0.000156 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095265 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 = 155.946 INNER LIMIT (NORMALIZED BY RADIUS) = 0.122 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19780.13 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.50, APC12 (Transition Start, Airfoil 1) AIRFOIL2: 4.90, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412