10x8M-LH (10x8M-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 0.5008 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 1.0845 0.0791 -0.1725 0.6060 0.1077 0.3184 10.1960 0.3921 0.6544 0.3015 -0.0009 -0.0232 0.1400 1.2500 1.6401 0.2894 -0.2274 0.5937 0.1904 0.3109 18.2110 0.3887 0.6402 0.3049 0.0012 -0.0255 0.2100 1.2625 2.1682 0.6020 -0.1786 0.5759 0.2513 0.3036 24.5246 0.3833 0.6043 0.3081 0.0071 -0.0282 0.2800 1.2668 2.6693 0.9943 -0.0340 0.5609 0.2937 0.2965 29.4732 0.3756 0.5540 0.3141 0.0202 -0.0312 0.3500 1.2543 3.1440 1.4593 0.1992 0.5455 0.3206 0.2895 33.5674 0.3631 0.4920 0.3305 0.0390 -0.0341 0.4200 1.2222 3.5928 2.0069 0.5214 0.5305 0.3352 0.2827 37.2524 0.3455 0.4230 0.3436 0.0644 -0.0359 0.4900 1.1676 4.0162 2.6850 0.9744 0.5166 0.3407 0.2760 41.0915 0.3222 0.3503 0.3499 0.0984 -0.0342 0.5600 1.0967 4.4148 3.5717 1.6649 0.5047 0.3402 0.2695 45.4291 0.2956 0.2805 0.3515 0.1388 -0.0260 0.6300 1.0500 4.7891 4.4765 2.5115 0.4956 0.3368 0.2631 48.5149 0.2763 0.2342 0.3515 0.1643 -0.0159 0.7000 1.0384 5.1396 5.1314 3.2219 0.4900 0.3338 0.2570 49.3993 0.2668 0.2145 0.3511 0.1678 -0.0086 0.7734 1.0554 5.4823 5.4823 3.6229 0.4869 0.3322 0.2507 48.4466 0.2646 0.2124 0.3503 0.1537 -0.0060 0.9053 1.0832 6.0357 6.0357 4.3054 0.4819 0.3288 0.2398 46.6987 0.2597 0.2075 0.3484 0.1293 -0.0012 1.0406 1.1064 6.5236 6.5236 4.9560 0.4776 0.3248 0.2292 44.9369 0.2536 0.2010 0.3458 0.1065 0.0040 1.1758 1.1264 6.9345 6.9345 5.5314 0.4736 0.3200 0.2192 43.1867 0.2469 0.1945 0.3424 0.0851 0.0087 1.3111 1.1442 7.2723 7.2723 6.0099 0.4699 0.3146 0.2099 41.4375 0.2401 0.1891 0.3384 0.0649 0.0126 1.4464 1.1597 7.5408 7.5408 6.3743 0.4662 0.3085 0.2011 39.6848 0.2332 0.1852 0.3337 0.0458 0.0158 1.5817 1.1729 7.7440 7.7440 6.6263 0.4623 0.3017 0.1929 37.9272 0.2263 0.1827 0.3283 0.0278 0.0184 1.7169 1.1839 7.8856 7.8856 6.8175 0.4578 0.2942 0.1854 36.1658 0.2195 0.1798 0.3222 0.0103 0.0214 1.8522 1.1926 7.9696 7.9696 6.9544 0.4526 0.2861 0.1784 34.4035 0.2128 0.1763 0.3154 -0.0068 0.0246 1.9875 1.1991 7.9998 7.9998 7.0377 0.4464 0.2773 0.1721 32.6441 0.2063 0.1726 0.3080 -0.0237 0.0282 2.1228 1.2032 8.0000 8.0000 7.0877 0.4391 0.2681 0.1663 30.9555 0.2001 0.1689 0.3001 -0.0404 0.0315 2.2580 1.2051 8.0000 8.0000 7.1320 0.4303 0.2582 0.1612 29.4174 0.1942 0.1651 0.2917 -0.0567 0.0338 2.3933 1.2048 8.0000 8.0000 7.1711 0.4198 0.2479 0.1566 28.0129 0.1887 0.1612 0.2828 -0.0728 0.0351 2.5286 1.2021 8.0000 8.0000 7.2045 0.4074 0.2371 0.1527 26.7270 0.1835 0.1573 0.2733 -0.0893 0.0355 2.6639 1.1972 8.0000 8.0000 7.2316 0.3928 0.2258 0.1493 25.5463 0.1788 0.1532 0.2633 -0.1063 0.0350 2.7991 1.1900 8.0000 8.0000 7.2514 0.3759 0.2141 0.1466 24.4593 0.1744 0.1492 0.2527 -0.1241 0.0336 2.9344 1.1806 8.0000 8.0000 7.2636 0.3563 0.2019 0.1444 23.4560 0.1705 0.1451 0.2415 -0.1431 0.0314 3.0697 1.1689 8.0000 8.0000 7.2750 0.3338 0.1893 0.1424 22.5276 0.1665 0.1407 0.2298 -0.1636 0.0283 3.2050 1.1549 8.0000 8.0000 7.2890 0.3082 0.1764 0.1405 21.6665 0.1622 0.1358 0.2175 -0.1859 0.0245 3.3402 1.1386 8.0000 8.0000 7.3056 0.2793 0.1630 0.1385 20.8659 0.1577 0.1306 0.2047 -0.2103 0.0198 3.4755 1.1201 8.0000 8.0000 7.3250 0.2468 0.1492 0.1365 20.1201 0.1529 0.1250 0.1913 -0.2371 0.0145 3.6108 1.0993 8.0000 8.0000 7.3475 0.2105 0.1351 0.1345 19.4237 0.1478 0.1190 0.1773 -0.2664 0.0084 3.7461 1.0763 8.0000 8.0000 7.3721 0.1701 0.1206 0.1325 18.7722 0.1426 0.1128 0.1628 -0.2987 0.0017 3.8813 1.0509 8.0000 8.0000 7.3985 0.1254 0.1057 0.1305 18.1616 0.1372 0.1064 0.1477 -0.3340 -0.0058 4.0166 1.0233 8.0000 8.0000 7.4283 0.0761 0.0905 0.1285 17.5882 0.1315 0.0998 0.1320 -0.3727 -0.0139 4.1519 0.9935 8.0000 8.0000 7.4618 0.0221 0.0749 0.1265 17.0489 0.1257 0.0930 0.1158 -0.4151 -0.0226 4.2872 0.9613 8.0000 8.0000 7.4969 -0.0369 0.0589 0.1245 16.5408 0.1197 0.0861 0.0990 -0.4613 -0.0320 4.4224 0.9269 8.0000 8.0000 7.5122 -0.1012 0.0425 0.1225 16.0613 0.1136 0.0790 0.0817 -0.5111 -0.0417 4.5577 0.8821 7.9973 7.9983 7.4085 -0.1747 0.0248 0.1206 15.6050 0.1063 0.0705 0.0613 -0.5649 -0.0537 4.6872 0.8106 7.9720 7.9774 6.9184 -0.2559 0.0064 0.1191 15.1562 0.0965 0.0588 0.0367 -0.6142 -0.0677 4.7179 0.7812 7.9620 7.9712 6.7410 -0.2814 0.0006 0.1191 15.0508 0.0930 0.0545 0.0288 -0.6264 -0.0718 4.7429 0.7507 7.9528 7.9667 6.5869 -0.3055 -0.0050 0.1192 14.9671 0.0895 0.0503 0.0213 -0.6370 -0.0755 4.7678 0.7134 7.9426 7.9632 6.4200 -0.3331 -0.0114 0.1194 14.8860 0.0852 0.0455 0.0127 -0.6480 -0.0794 4.7928 0.6691 7.9314 7.9613 6.2413 -0.3640 -0.0187 0.1198 14.8086 0.0802 0.0401 0.0032 -0.6593 -0.0834 4.8177 0.6184 7.9192 7.9615 6.0515 -0.3974 -0.0265 0.1203 14.7356 0.0744 0.0343 -0.0071 -0.6702 -0.0874 4.8427 0.5620 7.9060 7.9648 5.8522 -0.4327 -0.0346 0.1210 14.6687 0.0680 0.0285 -0.0177 -0.6806 -0.0911 4.8676 0.4989 7.8919 7.9735 5.6492 -0.4704 -0.0434 0.1219 14.6121 0.0608 0.0225 -0.0290 -0.6904 -0.0946 4.8926 0.4233 7.8767 7.9953 5.4630 -0.5137 -0.0534 0.1230 14.5787 0.0521 0.0163 -0.0418 -0.7004 -0.0979 4.9175 0.3155 7.8605 8.0650 5.3911 -0.5731 -0.0673 0.1243 14.6290 0.0392 0.0091 -0.0591 -0.7126 -0.1017 4.9400 0.0573 7.8451 8.6518 8.6518 -0.7105 -0.1015 0.1256 15.5753 0.0072 0.0000 -0.1015 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) = 0.112851 TOTAL WEIGHT (Kg) = 0.051179 TOTAL VOLUME (IN**3) = 1.838480 TOTAL PROJECTED AREA (IN**2) = 9.3634 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001350 MOMENT OF INERTIA (Kg-M**2) = 0.000152 STATIC MOMENT, ONE SIDE (IN-LB) = 0.093740 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 = 153.781 INNER LIMIT (NORMALIZED BY RADIUS) = 0.122 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19938.40 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