11x6M-LH (11x6M-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 1.2400 0.3759 0.0000 0.0000 0.6200 0.0000 0.3112 0.0000 0.3859 0.0000 0.3000 0.0000 0.0000 0.0700 1.2411 0.7281 0.0409 -0.2138 0.6197 0.0544 0.3052 5.3114 0.3788 0.6813 0.3009 0.0010 -0.0283 0.1400 1.2433 1.0689 0.1607 -0.3524 0.6190 0.1006 0.2993 10.3504 0.3722 0.6800 0.3033 0.0083 -0.0318 0.2100 1.2443 1.3984 0.3554 -0.4267 0.6182 0.1391 0.2936 15.0752 0.3653 0.6767 0.3067 0.0206 -0.0368 0.2800 1.2415 1.7164 0.6222 -0.4075 0.6173 0.1704 0.2879 19.4760 0.3575 0.6505 0.3099 0.0385 -0.0409 0.3500 1.2312 2.0231 0.9598 -0.2716 0.6167 0.1950 0.2824 23.5799 0.3477 0.5982 0.3128 0.0625 -0.0433 0.4200 1.2089 2.3183 1.3720 -0.0041 0.6165 0.2135 0.2770 27.4709 0.3348 0.5280 0.3158 0.0934 -0.0435 0.4900 1.1674 2.6022 1.8764 0.3935 0.6169 0.2264 0.2716 31.3607 0.3171 0.4468 0.3187 0.1332 -0.0402 0.5600 1.1062 2.8747 2.4980 0.9729 0.6182 0.2344 0.2664 35.3727 0.2947 0.3645 0.3207 0.1807 -0.0314 0.6300 1.0555 3.1358 3.1281 1.6504 0.6205 0.2379 0.2613 38.3175 0.2758 0.3028 0.3207 0.2188 -0.0200 0.7000 1.0282 3.3855 3.5690 2.1376 0.6240 0.2376 0.2563 39.0580 0.2636 0.2701 0.3179 0.2377 -0.0108 0.7743 1.0136 3.6382 3.8386 2.3752 0.6286 0.2351 0.2512 38.2727 0.2546 0.2541 0.3128 0.2450 -0.0041 0.9230 0.9889 4.1050 4.3346 2.8435 0.6380 0.2297 0.2412 36.7763 0.2385 0.2268 0.3027 0.2586 0.0070 1.0759 0.9692 4.5318 4.7886 3.3131 0.6477 0.2236 0.2315 35.3117 0.2243 0.2039 0.2924 0.2709 0.0155 1.2289 0.9548 4.9042 5.1856 3.7611 0.6570 0.2169 0.2223 33.8851 0.2122 0.1853 0.2823 0.2812 0.0217 1.3819 0.9451 5.2222 5.5259 4.1786 0.6657 0.2096 0.2136 32.4744 0.2019 0.1702 0.2722 0.2894 0.0260 1.5348 0.9395 5.4859 5.8097 4.5579 0.6733 0.2019 0.2055 31.0664 0.1930 0.1577 0.2622 0.2951 0.0287 1.6878 0.9374 5.6951 6.0372 4.8919 0.6797 0.1936 0.1979 29.6528 0.1855 0.1475 0.2522 0.2982 0.0302 1.8408 0.9382 5.8500 6.2089 5.1745 0.6844 0.1848 0.1908 28.2283 0.1790 0.1392 0.2421 0.2988 0.0307 1.9937 0.9412 5.9506 6.3249 5.4003 0.6872 0.1755 0.1842 26.7894 0.1734 0.1323 0.2320 0.2965 0.0305 2.1467 0.9459 5.9967 6.3856 5.5649 0.6877 0.1657 0.1782 25.3341 0.1686 0.1266 0.2218 0.2915 0.0297 2.2997 0.9516 6.0000 6.4028 5.6753 0.6856 0.1554 0.1727 23.8995 0.1644 0.1219 0.2115 0.2837 0.0282 2.4526 0.9577 6.0000 6.4167 5.7673 0.6806 0.1449 0.1678 22.6065 0.1607 0.1180 0.2011 0.2733 0.0255 2.6056 0.9636 6.0000 6.4308 5.8439 0.6724 0.1341 0.1634 21.4452 0.1574 0.1148 0.1904 0.2603 0.0218 2.7586 0.9687 6.0000 6.4452 5.9052 0.6606 0.1231 0.1595 20.3979 0.1545 0.1120 0.1795 0.2444 0.0172 2.9115 0.9723 6.0000 6.4601 5.9513 0.6449 0.1118 0.1561 19.4499 0.1518 0.1096 0.1684 0.2256 0.0118 3.0645 0.9739 6.0000 6.4758 5.9822 0.6250 0.1002 0.1533 18.5890 0.1493 0.1074 0.1570 0.2037 0.0058 3.2174 0.9727 6.0000 6.4925 5.9979 0.6006 0.0882 0.1510 17.8048 0.1469 0.1053 0.1453 0.1787 -0.0009 3.3704 0.9682 6.0000 6.5100 6.0000 0.5713 0.0759 0.1492 17.0881 0.1445 0.1030 0.1333 0.1505 -0.0081 3.5234 0.9597 6.0000 6.5273 6.0001 0.5368 0.0636 0.1475 16.4278 0.1415 0.1000 0.1208 0.1189 -0.0154 3.6763 0.9466 6.0000 6.5437 6.0001 0.4969 0.0512 0.1457 15.8168 0.1380 0.0961 0.1080 0.0840 -0.0229 3.8293 0.9284 6.0000 6.5594 6.0001 0.4511 0.0388 0.1440 15.2495 0.1337 0.0914 0.0948 0.0456 -0.0304 3.9823 0.9042 6.0000 6.5740 6.0001 0.3992 0.0263 0.1423 14.7208 0.1286 0.0856 0.0810 0.0037 -0.0379 4.1352 0.8737 6.0000 6.5874 6.0001 0.3409 0.0139 0.1405 14.2265 0.1228 0.0790 0.0668 -0.0418 -0.0454 4.2882 0.8360 6.0000 6.5993 6.0001 0.2757 0.0014 0.1388 13.7625 0.1160 0.0714 0.0521 -0.0909 -0.0529 4.4412 0.7906 6.0000 6.6094 6.0000 0.2035 -0.0112 0.1370 13.3254 0.1083 0.0631 0.0367 -0.1437 -0.0604 4.5941 0.7368 6.0000 6.6172 6.0000 0.1238 -0.0237 0.1353 12.9115 0.0997 0.0542 0.0208 -0.2003 -0.0678 4.7471 0.6741 5.9954 6.6176 5.9950 0.0364 -0.0364 0.1336 12.5094 0.0900 0.0448 0.0043 -0.2606 -0.0751 4.9001 0.6020 5.9553 6.6308 5.9155 -0.0591 -0.0481 0.1318 12.1541 0.0794 0.0353 -0.0127 -0.3248 -0.0823 5.0530 0.5200 5.8740 6.7219 5.7672 -0.1630 -0.0584 0.1301 11.9540 0.0676 0.0260 -0.0297 -0.3930 -0.0892 5.1995 0.4315 5.7575 6.9240 5.6091 -0.2707 -0.0672 0.1284 11.9663 0.0554 0.0177 -0.0459 -0.4619 -0.0953 5.2337 0.4093 5.7249 6.9907 5.5750 -0.2970 -0.0693 0.1280 12.0016 0.0524 0.0159 -0.0497 -0.4786 -0.0967 5.2614 0.3909 5.6969 7.0503 5.5490 -0.3186 -0.0710 0.1277 12.0392 0.0499 0.0144 -0.0528 -0.4922 -0.0978 5.2890 0.3722 5.6676 7.1150 5.5249 -0.3405 -0.0727 0.1274 12.0847 0.0474 0.0131 -0.0559 -0.5059 -0.0989 5.3167 0.3530 5.6370 7.1846 5.5028 -0.3628 -0.0744 0.1271 12.1377 0.0449 0.0117 -0.0590 -0.5197 -0.1000 5.3444 0.3332 5.6050 7.2681 5.4821 -0.3856 -0.0763 0.1268 12.2129 0.0422 0.0104 -0.0622 -0.5339 -0.1011 5.3721 0.3122 5.5717 7.3477 5.4653 -0.4100 -0.0785 0.1265 12.2808 0.0395 0.0091 -0.0657 -0.5491 -0.1025 5.3997 0.2876 5.5370 7.4309 5.4528 -0.4373 -0.0814 0.1262 12.3540 0.0363 0.0077 -0.0701 -0.5657 -0.1042 5.4274 0.2536 5.5010 7.5171 5.4804 -0.4702 -0.0859 0.1258 12.4312 0.0319 0.0060 -0.0763 -0.5837 -0.1066 5.4551 0.1970 5.4636 7.6041 5.6212 -0.5152 -0.0937 0.1255 12.5087 0.0247 0.0036 -0.0866 -0.6038 -0.1104 5.4800 0.0484 5.4288 5.4288 5.4288 -0.6058 -0.1180 0.1252 8.9599 0.0061 0.0000 -0.1180 0.0000 0.0000 RADIUS: 5.52 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.110033 TOTAL WEIGHT (Kg) = 0.049902 TOTAL VOLUME (IN**3) = 1.792578 TOTAL PROJECTED AREA (IN**2) = 9.0276 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001198 MOMENT OF INERTIA (Kg-M**2) = 0.000135 STATIC MOMENT, ONE SIDE (IN-LB) = 0.082938 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 = 97.120 INNER LIMIT (NORMALIZED BY RADIUS) = 0.112 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18334.16 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.