10x8 (10x8.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 1.0000 0.5000 0.0000 0.0000 0.5000 0.0000 0.4166 0.0000 0.4166 0.0000 0.1150 0.0000 0.0000 0.1200 0.9579 1.3730 0.0123 -0.4383 0.4941 0.0059 0.3965 0.9337 0.3798 0.3288 0.1194 0.0116 -0.0777 0.2400 0.9074 2.1920 0.0961 -0.8526 0.4886 0.0220 0.3771 3.6464 0.3422 0.3211 0.1314 0.0324 -0.0746 0.3600 0.8551 2.9570 0.3184 -1.1397 0.4837 0.0455 0.3585 8.0128 0.3066 0.3050 0.1487 0.0571 -0.0681 0.4800 0.8083 3.6680 0.7419 -1.1873 0.4797 0.0740 0.3407 13.8191 0.2754 0.2813 0.1694 0.0841 -0.0584 0.6000 0.7730 4.3250 1.4192 -0.8995 0.4767 0.1050 0.3237 20.6295 0.2502 0.2536 0.1918 0.1122 -0.0468 0.7200 0.7524 4.9280 2.3783 -0.2112 0.4751 0.1361 0.3074 27.7321 0.2313 0.2248 0.2142 0.1398 -0.0341 0.8400 0.7450 5.4770 3.5940 0.8747 0.4751 0.1649 0.2919 34.2534 0.2175 0.1976 0.2345 0.1655 -0.0214 0.9600 0.7458 5.9720 4.9498 2.2309 0.4768 0.1888 0.2771 39.3724 0.2067 0.1738 0.2508 0.1880 -0.0094 1.0800 0.7474 6.4130 6.2055 3.5539 0.4806 0.2054 0.2632 42.4424 0.1967 0.1548 0.2610 0.2058 0.0010 1.2000 0.7435 6.8000 7.0116 4.3685 0.4866 0.2124 0.2500 42.9212 0.1859 0.1414 0.2629 0.2179 0.0087 1.3199 0.7365 7.1328 7.3629 4.6886 0.4943 0.2119 0.2376 41.5991 0.1750 0.1302 0.2574 0.2259 0.0134 1.4383 0.7341 7.4084 7.6514 5.0981 0.5028 0.2097 0.2261 40.2540 0.1660 0.1172 0.2494 0.2329 0.0157 1.5566 0.7360 7.6313 7.8861 5.5613 0.5118 0.2062 0.2154 38.8808 0.1585 0.1039 0.2398 0.2388 0.0161 1.6748 0.7418 7.8017 8.0674 6.0110 0.5211 0.2013 0.2054 37.4746 0.1524 0.0925 0.2300 0.2432 0.0152 1.7931 0.7509 7.9197 8.1953 6.4150 0.5306 0.1952 0.1962 36.0325 0.1473 0.0845 0.2206 0.2455 0.0132 1.9114 0.7616 7.9853 8.2697 6.7027 0.5399 0.1880 0.1877 34.5510 0.1430 0.0805 0.2122 0.2464 0.0112 2.0297 0.7732 8.0000 8.2924 6.8826 0.5490 0.1798 0.1800 33.0336 0.1392 0.0795 0.2045 0.2462 0.0095 2.1479 0.7852 8.0000 8.2999 7.0495 0.5575 0.1707 0.1730 31.5912 0.1359 0.0790 0.1964 0.2454 0.0071 2.2662 0.7973 8.0000 8.3073 7.2201 0.5654 0.1608 0.1668 30.2602 0.1330 0.0787 0.1878 0.2440 0.0038 2.3845 0.8091 8.0000 8.3151 7.3906 0.5722 0.1501 0.1613 29.0303 0.1305 0.0785 0.1787 0.2420 -0.0004 2.5028 0.8201 8.0000 8.3235 7.5623 0.5780 0.1388 0.1566 27.8925 0.1284 0.0785 0.1690 0.2394 -0.0055 2.6210 0.8301 8.0000 8.3327 7.7245 0.5824 0.1267 0.1526 26.8386 0.1267 0.0786 0.1587 0.2361 -0.0115 2.7393 0.8386 8.0000 8.3432 7.8600 0.5851 0.1139 0.1494 25.8614 0.1253 0.0787 0.1476 0.2323 -0.0185 2.8576 0.8453 8.0000 8.3551 7.9558 0.5862 0.1005 0.1470 24.9544 0.1242 0.0787 0.1356 0.2280 -0.0266 2.9759 0.8497 8.0000 8.3686 7.9991 0.5852 0.0864 0.1453 24.1119 0.1234 0.0785 0.1226 0.2234 -0.0357 3.0941 0.8514 8.0000 8.3833 8.0003 0.5820 0.0719 0.1441 23.3265 0.1226 0.0782 0.1086 0.2181 -0.0458 3.2124 0.8501 8.0000 8.3972 8.0003 0.5764 0.0571 0.1429 22.5886 0.1215 0.0772 0.0943 0.2118 -0.0559 3.3307 0.8453 8.0000 8.4101 8.0003 0.5681 0.0421 0.1417 21.8938 0.1198 0.0757 0.0796 0.2045 -0.0661 3.4490 0.8368 8.0000 8.4220 8.0003 0.5571 0.0271 0.1405 21.2381 0.1176 0.0735 0.0646 0.1961 -0.0762 3.5672 0.8240 8.0000 8.4326 8.0003 0.5429 0.0120 0.1393 20.6177 0.1148 0.0707 0.0492 0.1865 -0.0862 3.6855 0.8066 8.0000 8.4418 8.0003 0.5255 -0.0032 0.1381 20.0293 0.1114 0.0672 0.0336 0.1757 -0.0960 3.8038 0.7842 8.0000 8.4492 8.0003 0.5046 -0.0183 0.1370 19.4698 0.1074 0.0630 0.0178 0.1636 -0.1056 3.9221 0.7564 8.0000 8.4545 8.0002 0.4801 -0.0333 0.1358 18.9359 0.1027 0.0581 0.0017 0.1503 -0.1149 4.0403 0.7228 8.0000 8.4571 8.0002 0.4516 -0.0482 0.1346 18.4248 0.0973 0.0527 -0.0146 0.1356 -0.1238 4.1586 0.6830 8.0000 8.4562 8.0002 0.4190 -0.0629 0.1334 17.9330 0.0911 0.0467 -0.0310 0.1195 -0.1322 4.2769 0.6366 7.9985 8.4500 7.9975 0.3821 -0.0774 0.1322 17.4555 0.0842 0.0403 -0.0476 0.1019 -0.1402 4.3952 0.5834 7.9550 8.4253 7.9252 0.3406 -0.0911 0.1310 16.9665 0.0765 0.0336 -0.0641 0.0828 -0.1476 4.5134 0.5231 7.8520 8.3925 7.7726 0.2944 -0.1037 0.1299 16.4855 0.0679 0.0269 -0.0802 0.0622 -0.1540 4.6317 0.4544 7.6892 8.3664 7.5640 0.2433 -0.1152 0.1287 16.0392 0.0585 0.0202 -0.0960 0.0403 -0.1594 4.7451 0.3795 7.4770 8.3498 7.3338 0.1893 -0.1257 0.1275 15.6452 0.0484 0.0140 -0.1108 0.0184 -0.1636 4.7753 0.3581 7.4115 8.3444 7.2705 0.1742 -0.1285 0.1272 15.5418 0.0456 0.0125 -0.1147 0.0124 -0.1646 4.8005 0.3396 7.3536 8.3382 7.2171 0.1612 -0.1308 0.1270 15.4530 0.0431 0.0112 -0.1180 0.0074 -0.1654 4.8258 0.3206 7.2929 8.3294 7.1637 0.1480 -0.1332 0.1267 15.3606 0.0406 0.0100 -0.1214 0.0023 -0.1661 4.8510 0.3012 7.2295 8.3167 7.1104 0.1346 -0.1356 0.1265 15.2622 0.0381 0.0089 -0.1248 -0.0028 -0.1669 4.8763 0.2807 7.1634 8.2982 7.0574 0.1203 -0.1383 0.1262 15.1546 0.0354 0.0077 -0.1284 -0.0083 -0.1677 4.9015 0.2555 7.0946 8.2794 7.0042 0.1017 -0.1420 0.1260 15.0475 0.0322 0.0064 -0.1333 -0.0159 -0.1691 4.9268 0.2232 7.0231 8.2406 7.0264 0.0766 -0.1476 0.1257 14.9067 0.0281 0.0049 -0.1401 -0.0270 -0.1715 4.9520 0.1793 6.9488 8.1832 7.1985 0.0403 -0.1560 0.1255 14.7353 0.0225 0.0032 -0.1502 -0.0438 -0.1756 4.9773 0.1025 6.8718 8.0983 8.2587 -0.0275 -0.1725 0.1252 14.5181 0.0128 0.0011 -0.1693 -0.0773 -0.1841 5.0000 0.0087 6.8002 6.8002 6.8002 -0.1123 -0.1935 0.1250 12.2137 0.0011 0.0000 -0.1935 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.068183 TOTAL WEIGHT (Kg) = 0.030922 TOTAL VOLUME (IN**3) = 1.110782 TOTAL PROJECTED AREA (IN**2) = 6.6200 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000697 MOMENT OF INERTIA (Kg-M**2) = 0.000079 STATIC MOMENT, ONE SIDE (IN-LB) = 0.051694 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 = 95.649 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13855.34 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.