8x8 (8x8.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 1.1960 0.0000 0.0000 0.4000 0.0000 0.4688 0.0000 0.3750 0.0000 0.0750 0.0000 0.0000 0.1160 0.7622 1.9624 0.0132 -0.5514 0.3948 0.0034 0.4658 1.0345 0.3550 0.2408 0.0781 0.0097 -0.1012 0.2320 0.7214 2.6830 0.1034 -1.0775 0.3906 0.0127 0.4570 4.0578 0.3297 0.2347 0.0864 0.0271 -0.1010 0.3480 0.6832 3.3578 0.3438 -1.4512 0.3875 0.0264 0.4423 8.9346 0.3022 0.2243 0.0985 0.0462 -0.0988 0.4640 0.6538 3.9868 0.7998 -1.5275 0.3855 0.0430 0.4217 15.3404 0.2757 0.2093 0.1131 0.0660 -0.0944 0.5800 0.6380 4.5701 1.5198 -1.1872 0.3845 0.0611 0.3952 22.6388 0.2522 0.1918 0.1287 0.0854 -0.0888 0.6960 0.6374 5.1076 2.5168 -0.3566 0.3844 0.0793 0.3629 29.9217 0.2313 0.1734 0.1438 0.1032 -0.0826 0.8120 0.6493 5.5993 3.7412 0.9485 0.3854 0.0964 0.3298 36.2525 0.2141 0.1556 0.1572 0.1184 -0.0763 0.9280 0.6681 6.0452 5.0542 2.5718 0.3873 0.1107 0.2999 40.9189 0.2004 0.1396 0.1674 0.1299 -0.0704 1.0440 0.6871 6.4454 6.2207 4.1876 0.3901 0.1211 0.2734 43.4808 0.1878 0.1256 0.1729 0.1365 -0.0653 1.1600 0.7009 6.7998 6.9480 5.3384 0.3937 0.1260 0.2500 43.6301 0.1752 0.1139 0.1727 0.1375 -0.0609 1.2745 0.7090 7.1047 7.2671 5.9693 0.3979 0.1265 0.2302 42.2238 0.1632 0.1036 0.1682 0.1352 -0.0574 1.3630 0.7137 7.3099 7.4782 6.4094 0.4012 0.1258 0.2171 41.1273 0.1549 0.0963 0.1643 0.1338 -0.0551 1.4501 0.7171 7.4856 7.6583 6.7982 0.4045 0.1243 0.2060 40.0489 0.1477 0.0899 0.1603 0.1326 -0.0532 1.5371 0.7191 7.6355 7.8121 7.1387 0.4076 0.1220 0.1968 38.9688 0.1415 0.0841 0.1559 0.1316 -0.0517 1.6241 0.7199 7.7597 7.9404 7.4268 0.4106 0.1188 0.1894 37.8866 0.1363 0.0792 0.1513 0.1308 -0.0504 1.7112 0.7194 7.8581 8.0438 7.6591 0.4132 0.1148 0.1838 36.8020 0.1322 0.0752 0.1464 0.1303 -0.0495 1.7982 0.7176 7.9307 8.1232 7.8327 0.4155 0.1100 0.1801 35.7150 0.1292 0.0722 0.1412 0.1300 -0.0488 1.8852 0.7145 7.9776 8.1776 7.9458 0.4173 0.1047 0.1773 34.6198 0.1267 0.0697 0.1357 0.1300 -0.0483 1.9723 0.7101 7.9987 8.2052 7.9969 0.4187 0.0991 0.1745 33.5095 0.1239 0.0674 0.1300 0.1303 -0.0480 2.0593 0.7044 8.0000 8.2120 8.0000 0.4194 0.0934 0.1718 32.4020 0.1210 0.0652 0.1241 0.1308 -0.0477 2.1463 0.6973 8.0000 8.2165 8.0002 0.4194 0.0875 0.1690 31.3525 0.1178 0.0629 0.1179 0.1313 -0.0478 2.2334 0.6888 8.0000 8.2199 8.0003 0.4186 0.0815 0.1662 30.3604 0.1145 0.0603 0.1115 0.1319 -0.0480 2.3204 0.6790 8.0000 8.2223 8.0005 0.4170 0.0754 0.1635 29.4212 0.1110 0.0576 0.1049 0.1324 -0.0483 2.4074 0.6678 8.0000 8.2235 8.0005 0.4144 0.0692 0.1607 28.5307 0.1073 0.0548 0.0981 0.1328 -0.0489 2.4945 0.6551 8.0000 8.2235 8.0004 0.4108 0.0629 0.1579 27.6851 0.1035 0.0519 0.0912 0.1328 -0.0496 2.5815 0.6410 8.0000 8.2223 8.0004 0.4060 0.0565 0.1552 26.8814 0.0995 0.0489 0.0840 0.1326 -0.0505 2.6686 0.6254 8.0000 8.2202 8.0004 0.4001 0.0500 0.1524 26.1169 0.0953 0.0458 0.0767 0.1319 -0.0516 2.7556 0.6083 8.0000 8.2171 8.0004 0.3929 0.0435 0.1496 25.3888 0.0910 0.0426 0.0692 0.1307 -0.0527 2.8426 0.5897 8.0000 8.2128 8.0004 0.3843 0.0369 0.1468 24.6941 0.0866 0.0393 0.0616 0.1289 -0.0540 2.9297 0.5696 8.0000 8.2072 8.0003 0.3743 0.0302 0.1441 24.0302 0.0821 0.0361 0.0538 0.1264 -0.0555 3.0167 0.5479 8.0000 8.2003 8.0003 0.3627 0.0235 0.1413 23.3948 0.0774 0.0328 0.0459 0.1232 -0.0570 3.1037 0.5246 8.0000 8.1917 8.0003 0.3496 0.0167 0.1385 22.7854 0.0727 0.0295 0.0378 0.1192 -0.0586 3.1908 0.4997 8.0000 8.1814 8.0003 0.3347 0.0098 0.1358 22.1997 0.0678 0.0263 0.0297 0.1143 -0.0603 3.2778 0.4732 8.0000 8.1688 8.0002 0.3180 0.0029 0.1330 21.6354 0.0629 0.0232 0.0214 0.1084 -0.0621 3.3648 0.4450 8.0000 8.1537 8.0002 0.2995 -0.0040 0.1302 21.0901 0.0580 0.0201 0.0131 0.1014 -0.0639 3.4519 0.4151 8.0000 8.1355 8.0001 0.2791 -0.0110 0.1275 20.5613 0.0529 0.0172 0.0046 0.0933 -0.0658 3.5389 0.3836 7.9927 8.1060 7.9928 0.2565 -0.0181 0.1247 20.0295 0.0478 0.0145 -0.0039 0.0840 -0.0678 3.6259 0.3503 7.9239 8.0100 7.9239 0.2319 -0.0252 0.1219 19.3710 0.0427 0.0118 -0.0125 0.0733 -0.0694 3.7130 0.3153 7.7823 7.8346 7.7823 0.2051 -0.0325 0.1192 18.5634 0.0376 0.0094 -0.0211 0.0612 -0.0709 3.7965 0.2801 7.5780 7.5889 7.5780 0.1772 -0.0395 0.1165 17.6477 0.0326 0.0073 -0.0295 0.0482 -0.0722 3.8202 0.2698 7.5079 7.5049 7.5079 0.1689 -0.0415 0.1157 17.3625 0.0312 0.0068 -0.0318 0.0442 -0.0725 3.8404 0.2609 7.4438 7.4281 7.4438 0.1617 -0.0432 0.1151 17.1102 0.0300 0.0063 -0.0339 0.0408 -0.0729 3.8606 0.2518 7.3758 7.3464 7.3758 0.1542 -0.0450 0.1145 16.8493 0.0288 0.0059 -0.0359 0.0372 -0.0732 3.8808 0.2406 7.3039 7.2597 7.3039 0.1447 -0.0473 0.1138 16.5796 0.0274 0.0054 -0.0386 0.0326 -0.0739 3.9010 0.2261 7.2281 7.1677 7.2296 0.1320 -0.0505 0.1132 16.3006 0.0256 0.0047 -0.0423 0.0263 -0.0751 3.9212 0.2074 7.1484 7.0703 7.1835 0.1152 -0.0547 0.1125 16.0120 0.0233 0.0040 -0.0472 0.0177 -0.0771 3.9414 0.1827 7.0647 6.9673 7.1679 0.0926 -0.0605 0.1119 15.7134 0.0204 0.0031 -0.0539 0.0060 -0.0800 3.9616 0.1471 6.9772 6.8582 7.2422 0.0593 -0.0690 0.1112 15.4041 0.0164 0.0020 -0.0637 -0.0113 -0.0846 3.9818 0.0804 6.8857 6.7420 7.9225 -0.0041 -0.0853 0.1106 15.0819 0.0089 0.0006 -0.0824 -0.0444 -0.0941 4.0000 0.0094 6.8000 6.8000 6.8000 -0.0720 -0.1022 0.1100 15.1397 0.0010 0.0000 -0.1022 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.16 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.043581 TOTAL WEIGHT (Kg) = 0.019764 TOTAL VOLUME (IN**3) = 0.709982 TOTAL PROJECTED AREA (IN**2) = 4.2012 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000237 MOMENT OF INERTIA (Kg-M**2) = 0.000027 STATIC MOMENT, ONE SIDE (IN-LB) = 0.024501 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 = 88.487 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28218.37 BASED ON MODULUS (MILLION) = 1.60 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.