10x4 (10x4.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 0.2500 0.0000 0.0000 0.5000 0.0000 0.4327 0.0000 0.4327 0.0000 0.1250 0.0000 0.0000 0.1200 0.9627 0.6865 0.0086 -0.4418 0.4941 0.0022 0.4120 0.6513 0.3967 0.3394 0.1266 0.0095 -0.0763 0.2400 0.9243 1.0960 0.0660 -0.8472 0.4886 0.0080 0.3921 2.5049 0.3624 0.3284 0.1309 0.0239 -0.0759 0.3600 0.8876 1.4785 0.2131 -1.1202 0.4837 0.0166 0.3729 5.3819 0.3310 0.3095 0.1368 0.0401 -0.0740 0.4800 0.8554 1.8340 0.4803 -1.1729 0.4797 0.0268 0.3545 9.0487 0.3033 0.2839 0.1436 0.0576 -0.0706 0.6000 0.8297 2.1625 0.8833 -0.9486 0.4767 0.0379 0.3370 13.1873 0.2796 0.2548 0.1505 0.0758 -0.0656 0.7200 0.8114 2.4640 1.4174 -0.4312 0.4751 0.0489 0.3202 17.3961 0.2598 0.2248 0.1569 0.0942 -0.0593 0.8400 0.7996 2.7385 2.0499 0.3399 0.4751 0.0589 0.3041 21.2256 0.2432 0.1963 0.1619 0.1122 -0.0520 0.9600 0.7921 2.9860 2.7142 1.2550 0.4768 0.0669 0.2889 24.2270 0.2288 0.1708 0.1647 0.1291 -0.0441 1.0800 0.7859 3.2065 3.3070 2.1242 0.4806 0.0720 0.2745 25.9814 0.2157 0.1497 0.1644 0.1444 -0.0365 1.2000 0.7785 3.4000 3.6918 2.6827 0.4866 0.0734 0.2608 26.0882 0.2030 0.1341 0.1601 0.1567 -0.0306 1.3199 0.7713 3.5664 3.8746 2.9140 0.4943 0.0716 0.2479 25.0417 0.1912 0.1233 0.1529 0.1663 -0.0270 1.4383 0.7676 3.7042 4.0248 3.1188 0.5028 0.0688 0.2360 24.0069 0.1811 0.1147 0.1456 0.1750 -0.0250 1.5566 0.7671 3.8156 4.1470 3.3007 0.5118 0.0652 0.2248 22.9783 0.1725 0.1076 0.1382 0.1830 -0.0242 1.6748 0.7693 3.9009 4.2416 3.4574 0.5211 0.0608 0.2144 21.9529 0.1649 0.1018 0.1306 0.1901 -0.0244 1.7931 0.7737 3.9599 4.3089 3.5866 0.5306 0.0556 0.2048 20.9294 0.1584 0.0971 0.1228 0.1965 -0.0255 1.9114 0.7800 3.9926 4.3490 3.6867 0.5399 0.0497 0.1959 19.9069 0.1528 0.0932 0.1148 0.2019 -0.0273 2.0297 0.7877 4.0000 4.3633 3.7567 0.5490 0.0432 0.1878 18.8882 0.1479 0.0901 0.1067 0.2065 -0.0298 2.1479 0.7964 4.0000 4.3700 3.8125 0.5575 0.0361 0.1804 17.9420 0.1437 0.0876 0.0984 0.2102 -0.0331 2.2662 0.8057 4.0000 4.3767 3.8611 0.5654 0.0287 0.1738 17.0863 0.1401 0.0856 0.0899 0.2132 -0.0373 2.3845 0.8151 4.0000 4.3839 3.9024 0.5722 0.0209 0.1680 16.3099 0.1370 0.0840 0.0812 0.2152 -0.0421 2.5028 0.8243 4.0000 4.3917 3.9364 0.5780 0.0126 0.1630 15.6039 0.1343 0.0828 0.0723 0.2163 -0.0476 2.6210 0.8327 4.0000 4.4005 3.9631 0.5824 0.0039 0.1587 14.9604 0.1321 0.0819 0.0632 0.2165 -0.0536 2.7393 0.8400 4.0000 4.4105 3.9826 0.5851 -0.0052 0.1551 14.3729 0.1303 0.0811 0.0539 0.2157 -0.0602 2.8576 0.8458 4.0000 4.4220 3.9949 0.5862 -0.0148 0.1523 13.8357 0.1288 0.0806 0.0444 0.2138 -0.0673 2.9759 0.8495 4.0000 4.4352 3.9999 0.5852 -0.0248 0.1503 13.3442 0.1277 0.0801 0.0346 0.2109 -0.0748 3.0941 0.8508 4.0000 4.4497 4.0000 0.5820 -0.0351 0.1488 12.8919 0.1266 0.0795 0.0247 0.2069 -0.0825 3.2124 0.8493 4.0000 4.4637 4.0000 0.5764 -0.0454 0.1473 12.4703 0.1251 0.0784 0.0145 0.2018 -0.0903 3.3307 0.8445 4.0000 4.4773 4.0000 0.5681 -0.0556 0.1459 12.0760 0.1232 0.0768 0.0041 0.1955 -0.0981 3.4490 0.8360 4.0000 4.4902 4.0001 0.5571 -0.0657 0.1444 11.7061 0.1207 0.0744 -0.0066 0.1880 -0.1058 3.5672 0.8233 4.0000 4.5023 4.0000 0.5429 -0.0757 0.1429 11.3581 0.1177 0.0715 -0.0175 0.1793 -0.1133 3.6855 0.8061 4.0000 4.5137 4.0000 0.5255 -0.0856 0.1414 11.0298 0.1140 0.0678 -0.0286 0.1693 -0.1208 3.8038 0.7838 4.0000 4.5241 4.0000 0.5046 -0.0953 0.1400 10.7189 0.1097 0.0635 -0.0400 0.1581 -0.1280 3.9221 0.7562 4.0000 4.5334 4.0000 0.4801 -0.1049 0.1385 10.4237 0.1047 0.0584 -0.0516 0.1455 -0.1351 4.0403 0.7227 4.0000 4.5413 4.0000 0.4516 -0.1142 0.1370 10.1423 0.0990 0.0528 -0.0635 0.1317 -0.1419 4.1586 0.6828 4.0000 4.5475 4.0000 0.4190 -0.1234 0.1355 9.8728 0.0925 0.0467 -0.0756 0.1165 -0.1486 4.2769 0.6363 3.9992 4.5515 3.9981 0.3821 -0.1324 0.1340 9.6131 0.0853 0.0401 -0.0881 0.0998 -0.1549 4.3952 0.5827 3.9775 4.5606 3.9484 0.3406 -0.1406 0.1326 9.3775 0.0772 0.0333 -0.1008 0.0818 -0.1611 4.5134 0.5217 3.9259 4.5959 3.8481 0.2944 -0.1477 0.1311 9.2054 0.0684 0.0265 -0.1135 0.0624 -0.1668 4.6317 0.4528 3.8445 4.6783 3.7203 0.2433 -0.1539 0.1296 9.1324 0.0587 0.0197 -0.1261 0.0414 -0.1719 4.7451 0.3789 3.7384 4.8213 3.5926 0.1893 -0.1592 0.1282 9.1857 0.0486 0.0137 -0.1380 0.0200 -0.1763 4.7753 0.3579 3.7056 4.8692 3.5611 0.1742 -0.1607 0.1278 9.2180 0.0457 0.0122 -0.1411 0.0141 -0.1774 4.8005 0.3398 3.6766 4.9127 3.5360 0.1612 -0.1619 0.1275 9.2508 0.0433 0.0110 -0.1438 0.0090 -0.1783 4.8258 0.3213 3.6463 4.9590 3.5122 0.1480 -0.1631 0.1272 9.2884 0.0409 0.0098 -0.1465 0.0039 -0.1792 4.8510 0.3024 3.6146 5.0075 3.4900 0.1346 -0.1645 0.1269 9.3297 0.0384 0.0087 -0.1493 -0.0013 -0.1801 4.8763 0.2818 3.5815 5.0579 3.4698 0.1196 -0.1660 0.1265 9.3740 0.0357 0.0075 -0.1523 -0.0072 -0.1812 4.9015 0.2563 3.5471 5.1097 3.4615 0.1000 -0.1684 0.1262 9.4204 0.0323 0.0062 -0.1563 -0.0156 -0.1827 4.9268 0.2236 3.5113 5.1612 3.4874 0.0735 -0.1720 0.1259 9.4658 0.0282 0.0047 -0.1618 -0.0277 -0.1849 4.9520 0.1791 3.4741 5.2106 3.5904 0.0355 -0.1776 0.1256 9.5069 0.0225 0.0031 -0.1697 -0.0461 -0.1884 4.9773 0.1008 3.4356 5.2555 4.1875 -0.0356 -0.1889 0.1253 9.5395 0.0126 0.0010 -0.1846 -0.0824 -0.1953 5.0000 0.0090 3.3998 3.3999 3.3998 -0.1204 -0.2032 0.1250 6.1766 0.0011 0.0000 -0.2032 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) = 0.069551 TOTAL WEIGHT (Kg) = 0.031543 TOTAL VOLUME (IN**3) = 1.133083 TOTAL PROJECTED AREA (IN**2) = 7.2696 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000711 MOMENT OF INERTIA (Kg-M**2) = 0.000080 STATIC MOMENT, ONE SIDE (IN-LB) = 0.052883 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 = 95.782 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18995.88 BASED ON MODULUS (MILLION) = 2.60 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.