18x8E (18x8E.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 1.2500 8.0000 0.0000 0.0000 0.6250 0.0000 0.3160 0.0000 0.3950 0.0000 0.2450 0.0000 0.0000 0.2000 1.1901 8.0000 0.0219 -0.3038 0.6149 0.0159 0.3141 0.9983 0.3738 0.4042 0.2543 0.0225 0.0472 0.4000 1.1344 8.0000 0.1702 -0.5389 0.6052 0.0589 0.3083 3.8744 0.3497 0.3921 0.2785 0.0429 0.0613 0.6000 1.0901 8.0000 0.5537 -0.5173 0.5964 0.1221 0.2986 8.3556 0.3255 0.3654 0.3131 0.0634 0.0852 0.8000 1.0644 8.0000 1.2500 -0.0884 0.5891 0.1989 0.2851 13.9654 0.3035 0.3303 0.3554 0.0829 0.1169 1.0000 1.0619 8.0000 2.2852 0.8322 0.5838 0.2828 0.2677 19.9861 0.2843 0.2923 0.4029 0.1006 0.1545 1.2000 1.0825 8.0000 3.6101 2.2274 0.5810 0.3671 0.2465 25.5854 0.2668 0.2553 0.4527 0.1156 0.1960 1.4000 1.1217 8.0000 5.0854 3.8577 0.5812 0.4454 0.2234 30.0331 0.2505 0.2219 0.5015 0.1275 0.2394 1.6000 1.1721 8.0000 6.4871 5.4490 0.5849 0.5110 0.2028 32.8336 0.2377 0.1946 0.5455 0.1356 0.2818 1.8000 1.2268 8.0000 7.5435 6.6879 0.5927 0.5573 0.1847 33.7030 0.2265 0.1752 0.5794 0.1382 0.3186 2.0000 1.2815 8.0000 7.9960 7.2951 0.6050 0.5779 0.1689 32.4686 0.2165 0.1667 0.5970 0.1316 0.3435 2.2010 1.3343 8.0000 8.0000 7.4044 0.6190 0.5773 0.1553 30.0487 0.2072 0.1666 0.5993 0.1164 0.3543 2.4190 1.3844 8.0000 8.0000 7.4959 0.6308 0.5680 0.1428 27.7604 0.1977 0.1666 0.5933 0.0994 0.3566 2.6379 1.4248 8.0000 8.0000 7.5721 0.6392 0.5502 0.1325 25.7650 0.1888 0.1662 0.5788 0.0828 0.3501 2.8569 1.4559 8.0000 8.0000 7.6329 0.6442 0.5304 0.1242 24.0212 0.1808 0.1657 0.5622 0.0666 0.3411 3.0759 1.4780 8.0000 8.0000 7.6779 0.6461 0.5104 0.1178 22.4869 0.1741 0.1652 0.5455 0.0509 0.3315 3.2948 1.4916 8.0000 8.0000 7.7066 0.6449 0.4904 0.1129 21.1283 0.1685 0.1649 0.5289 0.0357 0.3214 3.5138 1.4974 8.0000 8.0000 7.7190 0.6409 0.4704 0.1095 19.9182 0.1640 0.1649 0.5122 0.0213 0.3108 3.7328 1.4956 8.0000 8.0000 7.7151 0.6341 0.4505 0.1073 18.8344 0.1605 0.1648 0.4955 0.0076 0.2999 3.9517 1.4869 8.0000 8.0000 7.6946 0.6247 0.4307 0.1061 17.8589 0.1578 0.1646 0.4788 -0.0049 0.2889 4.1707 1.4716 8.0000 8.0000 7.6610 0.6130 0.4112 0.1055 16.9765 0.1553 0.1635 0.4620 -0.0165 0.2779 4.3897 1.4504 8.0000 8.0000 7.6245 0.5989 0.3922 0.1049 16.1750 0.1522 0.1609 0.4452 -0.0271 0.2672 4.6086 1.4236 8.0000 8.0000 7.5868 0.5827 0.3738 0.1044 15.4441 0.1486 0.1569 0.4283 -0.0367 0.2569 4.8276 1.3917 8.0000 8.0000 7.5495 0.5646 0.3559 0.1039 14.7749 0.1446 0.1514 0.4114 -0.0452 0.2469 5.0466 1.3553 8.0000 8.0000 7.5136 0.5446 0.3385 0.1034 14.1601 0.1401 0.1447 0.3945 -0.0526 0.2373 5.2655 1.3148 8.0000 8.0000 7.4805 0.5230 0.3215 0.1030 13.5936 0.1354 0.1369 0.3775 -0.0591 0.2280 5.4845 1.2708 8.0000 8.0000 7.4508 0.4999 0.3049 0.1025 13.0699 0.1303 0.1281 0.3604 -0.0646 0.2190 5.7034 1.2236 8.0000 8.0000 7.4259 0.4754 0.2887 0.1021 12.5844 0.1250 0.1187 0.3433 -0.0694 0.2102 5.9224 1.1738 8.0000 8.0000 7.4050 0.4497 0.2727 0.1018 12.1331 0.1195 0.1090 0.3261 -0.0736 0.2014 6.1414 1.1218 8.0000 8.0000 7.3847 0.4229 0.2568 0.1015 11.7127 0.1138 0.0993 0.3089 -0.0779 0.1923 6.3603 1.0682 8.0000 8.0000 7.3648 0.3952 0.2411 0.1012 11.3201 0.1081 0.0899 0.2916 -0.0822 0.1828 6.5793 1.0134 8.0000 8.0000 7.3452 0.3668 0.2255 0.1009 10.9526 0.1023 0.0808 0.2742 -0.0866 0.1730 6.7983 0.9579 8.0000 8.0000 7.3260 0.3378 0.2100 0.1007 10.6080 0.0964 0.0721 0.2567 -0.0913 0.1629 7.0172 0.9022 8.0000 8.0000 7.3068 0.3083 0.1945 0.1005 10.2841 0.0906 0.0639 0.2392 -0.0962 0.1523 7.2362 0.8467 8.0000 8.0000 7.2877 0.2785 0.1790 0.1003 9.9793 0.0849 0.0562 0.2216 -0.1015 0.1414 7.4552 0.7921 8.0000 8.0000 7.2687 0.2486 0.1635 0.1001 9.6918 0.0793 0.0492 0.2039 -0.1072 0.1300 7.6741 0.7387 8.0000 8.0000 7.2497 0.2187 0.1479 0.1000 9.4203 0.0739 0.0427 0.1861 -0.1134 0.1182 7.8931 0.6870 8.0000 8.0000 7.2304 0.1889 0.1323 0.0999 9.1635 0.0687 0.0370 0.1682 -0.1202 0.1060 8.1121 0.6375 8.0000 8.0000 7.2104 0.1594 0.1165 0.0999 8.9202 0.0637 0.0318 0.1503 -0.1276 0.0933 8.3310 0.5907 8.0000 8.0000 7.1891 0.1304 0.1005 0.0999 8.6893 0.0590 0.0273 0.1322 -0.1356 0.0801 8.5410 0.5489 8.0000 8.0000 7.1609 0.1032 0.0850 0.0999 8.4789 0.0548 0.0236 0.1147 -0.1441 0.0668 8.5955 0.5385 8.0000 8.0000 7.1284 0.0962 0.0809 0.0999 8.4259 0.0538 0.0227 0.1097 -0.1464 0.0629 8.6409 0.5298 8.0000 8.0000 7.0839 0.0902 0.0775 0.0999 8.3822 0.0529 0.0220 0.1053 -0.1485 0.0593 8.6864 0.5169 8.0000 8.0000 7.0215 0.0799 0.0734 0.0999 8.3390 0.0516 0.0209 0.0998 -0.1530 0.0550 8.7318 0.4978 8.0000 8.0000 6.9421 0.0633 0.0684 0.0999 8.2962 0.0497 0.0194 0.0929 -0.1610 0.0498 8.7773 0.4716 8.0000 8.0000 6.8077 0.0395 0.0624 0.0999 8.2538 0.0471 0.0174 0.0845 -0.1730 0.0437 8.8227 0.4363 8.0000 8.0000 6.4262 0.0066 0.0550 0.0999 8.2119 0.0436 0.0149 0.0744 -0.1902 0.0365 8.8682 0.3883 8.0000 8.0000 6.0090 -0.0390 0.0459 0.0999 8.1703 0.0388 0.0118 0.0620 -0.2144 0.0282 8.9136 0.3177 8.0000 8.0000 5.6052 -0.1071 0.0335 0.1000 8.1292 0.0318 0.0079 0.0457 -0.2510 0.0178 8.9591 0.1790 8.0000 8.0000 5.6608 -0.2428 0.0116 0.1000 8.0885 0.0179 0.0026 0.0179 -0.3249 0.0019 9.0000 0.0235 8.0000 8.0041 8.0040 -0.3955 -0.0120 0.1000 8.0563 0.0023 0.0000 -0.0120 0.0000 0.0000 RADIUS: 9.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.00 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.165885 TOTAL WEIGHT (Kg) = 0.075231 TOTAL VOLUME (IN**3) = 2.702477 TOTAL PROJECTED AREA (IN**2) = 19.2832 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005878 MOMENT OF INERTIA (Kg-M**2) = 0.000664 STATIC MOMENT, ONE SIDE (IN-LB) = 0.244116 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 = 73.406 INNER LIMIT (NORMALIZED BY RADIUS) = 0.069 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6146.40 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412