10x4M-LH (10x4M-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 0.8748 0.0000 0.0000 0.6200 0.0000 0.3113 0.0000 0.3859 0.0000 0.2200 0.0000 0.0000 0.0700 1.2408 1.0897 0.0396 -0.2268 0.6198 0.0508 0.3047 5.1388 0.3780 0.6179 0.2195 -0.0012 -0.0739 0.1400 1.2411 1.2970 0.1506 -0.3757 0.6193 0.0871 0.2982 9.7137 0.3701 0.6124 0.2179 0.0061 -0.0789 0.2100 1.2377 1.4966 0.3233 -0.4570 0.6188 0.1110 0.2919 13.7659 0.3613 0.6031 0.2155 0.0189 -0.0860 0.2800 1.2274 1.6886 0.5502 -0.4533 0.6183 0.1246 0.2857 17.3653 0.3507 0.5726 0.2119 0.0379 -0.0933 0.3500 1.2070 1.8729 0.8266 -0.3370 0.6181 0.1302 0.2797 20.5992 0.3376 0.5191 0.2077 0.0637 -0.0994 0.4200 1.1724 2.0496 1.1524 -0.1090 0.6183 0.1297 0.2738 23.5909 0.3210 0.4505 0.2036 0.0968 -0.1036 0.4900 1.1170 2.2186 1.5396 0.2316 0.6192 0.1251 0.2680 26.5687 0.2994 0.3737 0.1999 0.1391 -0.1039 0.5600 1.0365 2.3799 2.0175 0.7212 0.6207 0.1186 0.2624 29.8288 0.2719 0.2969 0.1962 0.1911 -0.0978 0.6300 0.9628 2.5336 2.5182 1.3242 0.6233 0.1121 0.2569 32.4629 0.2473 0.2380 0.1925 0.2361 -0.0868 0.7000 0.9246 2.6796 2.8514 1.7487 0.6269 0.1078 0.2515 32.9559 0.2325 0.2074 0.1887 0.2585 -0.0761 0.7735 0.9115 2.8246 3.0112 1.9077 0.6314 0.1055 0.2460 31.7822 0.2242 0.1942 0.1846 0.2649 -0.0678 0.9066 0.8918 3.0659 3.2755 2.1872 0.6398 0.1012 0.2364 29.8999 0.2108 0.1739 0.1772 0.2762 -0.0558 1.0432 0.8763 3.2847 3.5158 2.4631 0.6482 0.0964 0.2271 28.2089 0.1990 0.1572 0.1693 0.2867 -0.0469 1.1798 0.8653 3.4743 3.7250 2.7231 0.6562 0.0911 0.2183 26.6804 0.1889 0.1437 0.1613 0.2958 -0.0407 1.3163 0.8581 3.6348 3.9034 2.9631 0.6635 0.0851 0.2100 25.2648 0.1802 0.1327 0.1531 0.3030 -0.0366 1.4529 0.8543 3.7662 4.0512 3.1791 0.6698 0.0786 0.2022 23.9304 0.1728 0.1239 0.1447 0.3082 -0.0344 1.5895 0.8534 3.8684 4.1687 3.3676 0.6749 0.0714 0.1950 22.6560 0.1664 0.1166 0.1361 0.3112 -0.0336 1.7261 0.8548 3.9414 4.2562 3.5257 0.6784 0.0637 0.1882 21.4269 0.1609 0.1108 0.1272 0.3119 -0.0340 1.8627 0.8580 3.9853 4.3137 3.6507 0.6802 0.0554 0.1820 20.2328 0.1562 0.1060 0.1181 0.3103 -0.0354 1.9993 0.8625 4.0000 4.3416 3.7404 0.6798 0.0464 0.1763 19.0660 0.1520 0.1020 0.1088 0.3062 -0.0377 2.1359 0.8677 4.0000 4.3545 3.8067 0.6771 0.0371 0.1711 17.9770 0.1484 0.0988 0.0992 0.2997 -0.0410 2.2724 0.8731 4.0000 4.3673 3.8632 0.6717 0.0275 0.1664 17.0076 0.1453 0.0962 0.0894 0.2907 -0.0453 2.4090 0.8781 4.0000 4.3804 3.9099 0.6634 0.0175 0.1622 16.1400 0.1424 0.0939 0.0794 0.2792 -0.0504 2.5456 0.8823 4.0000 4.3937 3.9469 0.6519 0.0072 0.1585 15.3602 0.1399 0.0920 0.0690 0.2651 -0.0564 2.6822 0.8850 4.0000 4.4075 3.9741 0.6369 -0.0034 0.1554 14.6563 0.1375 0.0903 0.0584 0.2483 -0.0630 2.8188 0.8858 4.0000 4.4220 3.9916 0.6182 -0.0143 0.1527 14.0187 0.1353 0.0886 0.0475 0.2287 -0.0702 2.9554 0.8841 4.0000 4.4373 3.9996 0.5954 -0.0255 0.1506 13.4395 0.1331 0.0869 0.0363 0.2063 -0.0779 3.0920 0.8793 4.0000 4.4533 4.0000 0.5684 -0.0369 0.1489 12.9107 0.1309 0.0849 0.0248 0.1810 -0.0859 3.2286 0.8710 4.0000 4.4687 4.0000 0.5367 -0.0483 0.1471 12.4232 0.1282 0.0823 0.0131 0.1527 -0.0941 3.3651 0.8585 4.0000 4.4834 4.0000 0.5002 -0.0597 0.1454 11.9718 0.1249 0.0791 0.0010 0.1214 -0.1023 3.5017 0.8414 4.0000 4.4972 4.0000 0.4585 -0.0709 0.1437 11.5522 0.1209 0.0750 -0.0114 0.0870 -0.1104 3.6383 0.8191 4.0000 4.5101 4.0000 0.4114 -0.0820 0.1420 11.1607 0.1163 0.0703 -0.0241 0.0495 -0.1185 3.7749 0.7910 4.0000 4.5219 4.0000 0.3586 -0.0930 0.1403 10.7939 0.1110 0.0648 -0.0372 0.0089 -0.1264 3.9115 0.7566 4.0000 4.5322 4.0000 0.2998 -0.1039 0.1386 10.4487 0.1049 0.0586 -0.0506 -0.0350 -0.1342 4.0481 0.7155 4.0000 4.5408 4.0000 0.2347 -0.1145 0.1369 10.1223 0.0979 0.0518 -0.0643 -0.0821 -0.1419 4.1847 0.6669 4.0000 4.5472 4.0000 0.1631 -0.1250 0.1352 9.8119 0.0902 0.0445 -0.0784 -0.1325 -0.1493 4.3212 0.6105 3.9955 4.5569 3.9830 0.0847 -0.1350 0.1335 9.5273 0.0815 0.0368 -0.0928 -0.1862 -0.1566 4.4578 0.5458 3.9616 4.5964 3.8989 -0.0008 -0.1438 0.1318 9.3192 0.0719 0.0291 -0.1075 -0.2434 -0.1637 4.5944 0.4723 3.8946 4.6984 3.7751 -0.0936 -0.1513 0.1301 9.2442 0.0614 0.0215 -0.1220 -0.3040 -0.1701 4.7252 0.3931 3.7993 4.8868 3.6520 -0.1897 -0.1575 0.1284 9.3470 0.0505 0.0147 -0.1356 -0.3652 -0.1757 4.7562 0.3730 3.7723 4.9453 3.6263 -0.2135 -0.1590 0.1280 9.3964 0.0478 0.0132 -0.1388 -0.3802 -0.1769 4.7813 0.3563 3.7491 4.9970 3.6069 -0.2331 -0.1602 0.1277 9.4438 0.0455 0.0121 -0.1414 -0.3925 -0.1779 4.8065 0.3393 3.7248 5.0522 3.5892 -0.2530 -0.1614 0.1274 9.4971 0.0432 0.0109 -0.1440 -0.4049 -0.1789 4.8316 0.3219 3.6993 5.1109 3.5733 -0.2732 -0.1627 0.1271 9.5565 0.0409 0.0098 -0.1467 -0.4174 -0.1799 4.8568 0.3038 3.6727 5.1727 3.5595 -0.2939 -0.1641 0.1268 9.6206 0.0385 0.0087 -0.1495 -0.4303 -0.1809 4.8819 0.2846 3.6451 5.2371 3.5480 -0.3162 -0.1657 0.1265 9.6889 0.0360 0.0076 -0.1525 -0.4441 -0.1821 4.9071 0.2619 3.6162 5.3036 3.5448 -0.3412 -0.1679 0.1262 9.7603 0.0330 0.0065 -0.1561 -0.4591 -0.1835 4.9322 0.2306 3.5863 5.3714 3.5762 -0.3713 -0.1712 0.1258 9.8332 0.0290 0.0050 -0.1612 -0.4755 -0.1855 4.9574 0.1789 3.5552 5.4383 3.7194 -0.4125 -0.1771 0.1255 9.9038 0.0225 0.0030 -0.1696 -0.4938 -0.1886 4.9800 0.0452 3.5263 3.5263 3.5263 -0.4947 -0.1956 0.1252 6.4299 0.0057 0.0000 -0.1956 0.0000 0.0000 RADIUS: 5.01 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) = 0.085957 TOTAL WEIGHT (Kg) = 0.038983 TOTAL VOLUME (IN**3) = 1.400344 TOTAL PROJECTED AREA (IN**2) = 7.8291 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000744 MOMENT OF INERTIA (Kg-M**2) = 0.000084 STATIC MOMENT, ONE SIDE (IN-LB) = 0.056960 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 = 97.477 INNER LIMIT (NORMALIZED BY RADIUS) = 0.124 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19840.12 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.