14x10E (14x10E.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 0.8000 0.9120 0.0000 0.0000 0.4000 0.0000 0.4162 0.0000 0.3330 0.0000 0.1700 0.0000 0.0000 0.1200 0.7602 2.2241 0.0177 -0.3120 0.3949 0.0145 0.4145 1.3474 0.3151 0.2174 0.1799 0.0151 0.0085 0.2400 0.7174 3.4339 0.1407 -0.6089 0.3917 0.0542 0.4093 5.3288 0.2936 0.2164 0.2066 0.0347 0.0236 0.3600 0.6807 4.5415 0.4722 -0.7392 0.3904 0.1126 0.4007 11.7909 0.2727 0.2088 0.2449 0.0579 0.0492 0.4800 0.6602 5.5469 1.1097 -0.5222 0.3911 0.1839 0.3885 20.2004 0.2565 0.1949 0.2909 0.0828 0.0832 0.6000 0.6631 6.4500 2.1276 0.1922 0.3938 0.2625 0.3729 29.4393 0.2473 0.1781 0.3419 0.1075 0.1226 0.7200 0.6902 7.2509 3.5431 1.4888 0.3984 0.3425 0.3539 38.0678 0.2442 0.1611 0.3950 0.1305 0.1644 0.8400 0.7357 7.9495 5.2665 3.2573 0.4050 0.4182 0.3313 44.9385 0.2438 0.1461 0.4479 0.1499 0.2055 0.9600 0.7899 8.5459 7.0639 5.1842 0.4136 0.4839 0.3054 49.5062 0.2413 0.1344 0.4976 0.1644 0.2427 1.0800 0.8435 9.0401 8.5762 6.9031 0.4241 0.5339 0.2799 51.6475 0.2361 0.1271 0.5395 0.1722 0.2728 1.2000 0.8895 9.4320 9.4279 7.9778 0.4367 0.5623 0.2569 51.3493 0.2285 0.1245 0.5662 0.1722 0.2920 1.3233 0.9291 9.7283 9.7283 8.4352 0.4501 0.5743 0.2357 49.4796 0.2190 0.1246 0.5787 0.1657 0.3028 1.5038 0.9826 9.9671 9.9671 8.9002 0.4668 0.5850 0.2088 46.5298 0.2051 0.1236 0.5903 0.1526 0.3153 1.6876 1.0320 10.0000 10.0000 9.1491 0.4805 0.5875 0.1860 43.3224 0.1920 0.1219 0.5941 0.1355 0.3239 1.8714 1.0750 10.0000 10.0000 9.3257 0.4908 0.5815 0.1676 40.3801 0.1801 0.1199 0.5898 0.1175 0.3254 2.0552 1.1091 10.0000 10.0000 9.4623 0.4979 0.5676 0.1529 37.7546 0.1696 0.1179 0.5778 0.0999 0.3201 2.2390 1.1348 10.0000 10.0000 9.5588 0.5021 0.5515 0.1415 35.4068 0.1606 0.1163 0.5639 0.0828 0.3131 2.4228 1.1524 10.0000 10.0000 9.6254 0.5033 0.5353 0.1330 33.3016 0.1532 0.1147 0.5499 0.0671 0.3070 2.6066 1.1625 10.0000 10.0000 9.6675 0.5019 0.5189 0.1268 31.4081 0.1474 0.1133 0.5359 0.0525 0.3013 2.7903 1.1655 10.0000 10.0000 9.6897 0.4978 0.5025 0.1226 29.6995 0.1428 0.1119 0.5218 0.0390 0.2958 2.9741 1.1619 10.0000 10.0000 9.6967 0.4914 0.4862 0.1197 28.1526 0.1391 0.1105 0.5077 0.0264 0.2905 3.1579 1.1521 10.0000 10.0000 9.6991 0.4826 0.4699 0.1174 26.7474 0.1353 0.1083 0.4936 0.0148 0.2852 3.3417 1.1367 10.0000 10.0000 9.7008 0.4718 0.4538 0.1153 25.4669 0.1310 0.1053 0.4795 0.0040 0.2801 3.5255 1.1161 10.0000 10.0000 9.6995 0.4589 0.4380 0.1132 24.2962 0.1264 0.1014 0.4654 -0.0061 0.2750 3.7093 1.0908 10.0000 10.0000 9.6897 0.4442 0.4224 0.1113 23.2227 0.1214 0.0968 0.4512 -0.0153 0.2700 3.8931 1.0612 10.0000 10.0000 9.6739 0.4279 0.4072 0.1096 22.2354 0.1163 0.0916 0.4371 -0.0237 0.2651 4.0769 1.0278 10.0000 10.0000 9.6574 0.4100 0.3923 0.1079 21.3248 0.1109 0.0858 0.4228 -0.0314 0.2603 4.2607 0.9911 10.0000 10.0000 9.6414 0.3907 0.3777 0.1064 20.4828 0.1055 0.0797 0.4086 -0.0383 0.2556 4.4445 0.9516 10.0000 10.0000 9.6257 0.3702 0.3634 0.1051 19.7022 0.1000 0.0734 0.3942 -0.0447 0.2508 4.6283 0.9098 10.0000 10.0000 9.6116 0.3486 0.3493 0.1038 18.9768 0.0945 0.0669 0.3799 -0.0504 0.2460 4.8121 0.8660 10.0000 10.0000 9.5955 0.3260 0.3354 0.1028 18.3012 0.0890 0.0604 0.3654 -0.0557 0.2411 4.9959 0.8208 10.0000 10.0000 9.5821 0.3027 0.3217 0.1018 17.6705 0.0836 0.0540 0.3509 -0.0606 0.2360 5.1797 0.7746 10.0000 10.0000 9.5715 0.2787 0.3082 0.1010 17.0806 0.0782 0.0479 0.3363 -0.0652 0.2306 5.3634 0.7280 10.0000 10.0000 9.5610 0.2542 0.2947 0.1003 16.5277 0.0730 0.0421 0.3216 -0.0699 0.2248 5.5472 0.6814 10.0000 10.0000 9.5503 0.2294 0.2812 0.0997 16.0086 0.0679 0.0368 0.3069 -0.0748 0.2184 5.7310 0.6352 10.0000 10.0000 9.5391 0.2043 0.2676 0.0993 15.5204 0.0631 0.0319 0.2921 -0.0798 0.2114 5.9148 0.5899 10.0000 10.0000 9.5272 0.1792 0.2541 0.0990 15.0603 0.0584 0.0274 0.2772 -0.0852 0.2039 6.0986 0.5461 10.0000 10.0000 9.5138 0.1542 0.2404 0.0989 14.6262 0.0540 0.0235 0.2622 -0.0910 0.1958 6.2824 0.5041 10.0000 10.0000 9.4985 0.1295 0.2267 0.0988 14.2159 0.0498 0.0200 0.2472 -0.0972 0.1871 6.4662 0.4645 10.0000 10.0000 9.4809 0.1051 0.2128 0.0989 13.8275 0.0460 0.0170 0.2320 -0.1040 0.1777 6.6423 0.4292 10.0000 10.0000 9.4053 0.0823 0.1994 0.0992 13.4746 0.0426 0.0145 0.2167 -0.1110 0.1672 6.6854 0.4209 10.0000 10.0000 9.3584 0.0768 0.1961 0.0993 13.3909 0.0418 0.0140 0.2126 -0.1128 0.1641 6.7207 0.4143 10.0000 10.0000 9.3091 0.0722 0.1933 0.0993 13.3229 0.0411 0.0136 0.2092 -0.1144 0.1614 6.7561 0.4045 10.0000 10.0000 9.2488 0.0646 0.1898 0.0994 13.2557 0.0402 0.0129 0.2048 -0.1176 0.1582 6.7914 0.3898 10.0000 10.0000 9.1034 0.0520 0.1852 0.0995 13.1891 0.0388 0.0120 0.1991 -0.1236 0.1540 6.8268 0.3695 10.0000 10.0000 8.8447 0.0338 0.1793 0.0996 13.1232 0.0368 0.0108 0.1918 -0.1327 0.1490 6.8621 0.3420 10.0000 10.0000 8.5751 0.0086 0.1717 0.0996 13.0579 0.0341 0.0093 0.1828 -0.1456 0.1429 6.8975 0.3046 10.0000 10.0000 8.3035 -0.0264 0.1619 0.0997 12.9932 0.0304 0.0074 0.1712 -0.1640 0.1354 6.9328 0.2495 10.0000 10.0000 8.0798 -0.0788 0.1482 0.0998 12.9292 0.0249 0.0050 0.1554 -0.1919 0.1257 6.9682 0.1411 10.0000 10.0000 8.3552 -0.1833 0.1227 0.0999 12.8658 0.0141 0.0016 0.1265 -0.2483 0.1093 7.0000 0.0184 10.0000 10.0050 10.0050 -0.3021 0.0944 0.1000 12.8155 0.0018 0.0000 0.0944 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.079639 TOTAL WEIGHT (Kg) = 0.036117 TOTAL VOLUME (IN**3) = 1.297419 TOTAL PROJECTED AREA (IN**2) = 10.4966 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001755 MOMENT OF INERTIA (Kg-M**2) = 0.000198 STATIC MOMENT, ONE SIDE (IN-LB) = 0.094277 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 = 73.634 INNER LIMIT (NORMALIZED BY RADIUS) = 0.057 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9048.64 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.20, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.12, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412