10x10 (10x10.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 0.6240 0.0000 0.0000 0.5000 0.0000 0.3472 0.0000 0.3472 0.0000 0.0850 0.0000 0.0000 0.1200 0.9565 1.7154 0.0141 -0.5627 0.4941 0.0061 0.3386 1.0676 0.3239 0.3670 0.0903 0.0107 -0.1268 0.2400 0.9024 2.7392 0.1104 -1.0989 0.4886 0.0225 0.3303 4.1883 0.2980 0.3565 0.1045 0.0336 -0.1225 0.3600 0.8463 3.6956 0.3680 -1.4913 0.4837 0.0464 0.3221 9.2408 0.2725 0.3372 0.1252 0.0604 -0.1133 0.4800 0.7973 4.5844 0.8654 -1.6063 0.4797 0.0753 0.3140 16.0109 0.2504 0.3101 0.1501 0.0897 -0.1000 0.6000 0.7633 5.4058 1.6768 -1.3182 0.4767 0.1066 0.3062 23.9786 0.2337 0.2788 0.1772 0.1201 -0.0845 0.7200 0.7480 6.1596 2.8534 -0.5243 0.4751 0.1377 0.2986 32.2408 0.2234 0.2466 0.2041 0.1500 -0.0682 0.8400 0.7492 6.8459 4.3842 0.8054 0.4751 0.1662 0.2912 39.7156 0.2181 0.2166 0.2286 0.1777 -0.0526 0.9600 0.7593 7.4647 6.1340 2.5424 0.4768 0.1894 0.2839 45.4809 0.2156 0.1909 0.2484 0.2015 -0.0387 1.0800 0.7688 8.0160 7.7826 4.3051 0.4806 0.2049 0.2769 48.9140 0.2129 0.1713 0.2609 0.2195 -0.0274 1.2000 0.7690 8.4998 8.8410 5.4521 0.4866 0.2101 0.2700 49.5415 0.2076 0.1586 0.2638 0.2304 -0.0196 1.3199 0.7628 8.9158 9.2923 5.9166 0.4943 0.2076 0.2633 48.2517 0.2009 0.1507 0.2595 0.2363 -0.0149 1.4383 0.7600 9.2604 9.6650 6.3736 0.5028 0.2037 0.2569 46.9234 0.1953 0.1440 0.2544 0.2414 -0.0119 1.5566 0.7603 9.5391 9.9701 6.8274 0.5118 0.1987 0.2507 45.5512 0.1906 0.1383 0.2484 0.2459 -0.0102 1.6748 0.7633 9.7521 10.2079 7.2682 0.5211 0.1925 0.2447 44.1284 0.1868 0.1332 0.2415 0.2495 -0.0099 1.7931 0.7684 9.8997 10.3781 7.6841 0.5306 0.1853 0.2389 42.6499 0.1836 0.1288 0.2340 0.2522 -0.0105 1.9114 0.7753 9.9816 10.4809 8.0626 0.5399 0.1770 0.2332 41.1115 0.1808 0.1248 0.2256 0.2540 -0.0120 2.0297 0.7837 10.0000 10.5181 8.3919 0.5490 0.1678 0.2278 39.5150 0.1785 0.1211 0.2166 0.2548 -0.0143 2.1479 0.7929 10.0000 10.5356 8.6979 0.5575 0.1578 0.2225 37.9776 0.1764 0.1177 0.2069 0.2549 -0.0175 2.2662 0.8026 10.0000 10.5521 8.9883 0.5654 0.1472 0.2174 36.5411 0.1745 0.1146 0.1965 0.2545 -0.0219 2.3845 0.8124 10.0000 10.5677 9.2558 0.5722 0.1360 0.2125 35.1974 0.1727 0.1117 0.1856 0.2535 -0.0272 2.5028 0.8219 10.0000 10.5824 9.4932 0.5780 0.1242 0.2078 33.9389 0.1708 0.1090 0.1740 0.2518 -0.0334 2.6210 0.8306 10.0000 10.5964 9.6934 0.5824 0.1120 0.2033 32.7587 0.1688 0.1066 0.1619 0.2494 -0.0404 2.7393 0.8382 10.0000 10.6096 9.8492 0.5851 0.0993 0.1989 31.6506 0.1667 0.1044 0.1494 0.2463 -0.0482 2.8576 0.8441 10.0000 10.6221 9.9533 0.5862 0.0863 0.1948 30.6088 0.1644 0.1024 0.1363 0.2424 -0.0566 2.9759 0.8480 10.0000 10.6340 9.9987 0.5852 0.0729 0.1908 29.6281 0.1618 0.1007 0.1227 0.2378 -0.0656 3.0941 0.8495 10.0000 10.6451 10.0002 0.5820 0.0593 0.1869 28.7034 0.1588 0.0989 0.1088 0.2323 -0.0750 3.2124 0.8482 10.0000 10.6550 10.0005 0.5764 0.0455 0.1831 27.8291 0.1553 0.0965 0.0944 0.2257 -0.0844 3.3307 0.8435 10.0000 10.6636 10.0007 0.5681 0.0316 0.1793 27.0013 0.1512 0.0934 0.0796 0.2180 -0.0936 3.4490 0.8351 10.0000 10.6709 10.0007 0.5571 0.0177 0.1754 26.2163 0.1465 0.0895 0.0646 0.2091 -0.1027 3.5672 0.8225 10.0000 10.6766 10.0006 0.5429 0.0037 0.1716 25.4705 0.1411 0.0850 0.0492 0.1990 -0.1115 3.6855 0.8054 10.0000 10.6808 10.0006 0.5255 -0.0102 0.1677 24.7609 0.1351 0.0797 0.0336 0.1876 -0.1199 3.8038 0.7832 10.0000 10.6831 10.0005 0.5046 -0.0241 0.1639 24.0844 0.1284 0.0736 0.0178 0.1751 -0.1280 3.9221 0.7557 10.0000 10.6835 10.0004 0.4801 -0.0380 0.1600 23.4382 0.1209 0.0670 0.0017 0.1611 -0.1356 4.0403 0.7222 10.0000 10.6817 10.0003 0.4516 -0.0517 0.1562 22.8197 0.1128 0.0598 -0.0146 0.1459 -0.1427 4.1586 0.6825 10.0000 10.6771 10.0002 0.4190 -0.0653 0.1523 22.2262 0.1040 0.0521 -0.0310 0.1293 -0.1493 4.2769 0.6360 9.9981 10.6684 9.9968 0.3821 -0.0787 0.1485 21.6531 0.0944 0.0442 -0.0475 0.1113 -0.1553 4.3952 0.5827 9.9438 10.6398 9.9069 0.3406 -0.0914 0.1447 21.0707 0.0843 0.0361 -0.0640 0.0918 -0.1606 4.5134 0.5221 9.8149 10.6030 9.7187 0.2944 -0.1029 0.1408 20.5001 0.0735 0.0282 -0.0799 0.0706 -0.1648 4.6317 0.4537 9.6114 10.5770 9.4620 0.2433 -0.1135 0.1370 19.9735 0.0621 0.0207 -0.0952 0.0480 -0.1680 4.7451 0.3802 9.3461 10.5714 9.1772 0.1893 -0.1233 0.1333 19.5230 0.0507 0.0142 -0.1096 0.0249 -0.1701 4.7753 0.3593 9.2642 10.5726 9.0982 0.1742 -0.1260 0.1323 19.4112 0.0475 0.0126 -0.1135 0.0186 -0.1706 4.8005 0.3413 9.1917 10.5739 9.0312 0.1612 -0.1282 0.1315 19.3188 0.0449 0.0113 -0.1167 0.0132 -0.1709 4.8258 0.3229 9.1159 10.5750 8.9640 0.1480 -0.1305 0.1307 19.2271 0.0422 0.0100 -0.1200 0.0078 -0.1713 4.8510 0.3040 9.0366 10.5752 8.8965 0.1346 -0.1329 0.1298 19.1347 0.0395 0.0088 -0.1233 0.0022 -0.1716 4.8763 0.2839 8.9540 10.5739 8.8292 0.1201 -0.1356 0.1290 19.0405 0.0366 0.0077 -0.1269 -0.0037 -0.1721 4.9015 0.2589 8.8679 10.5702 8.7625 0.1011 -0.1399 0.1282 18.9433 0.0332 0.0063 -0.1322 -0.0121 -0.1734 4.9268 0.2266 8.7785 10.5623 8.7288 0.0755 -0.1464 0.1274 18.8399 0.0289 0.0048 -0.1399 -0.0240 -0.1761 4.9520 0.1822 8.6856 10.5474 8.7808 0.0386 -0.1567 0.1266 18.7260 0.0231 0.0031 -0.1517 -0.0419 -0.1809 4.9773 0.1038 8.5893 10.5226 9.3346 -0.0304 -0.1778 0.1257 18.5968 0.0130 0.0010 -0.1750 -0.0772 -0.1920 5.0000 0.0090 8.4998 8.4998 8.4998 -0.1152 -0.2049 0.1250 15.1394 0.0011 0.0000 -0.2049 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) = 0.081317 TOTAL WEIGHT (Kg) = 0.036879 TOTAL VOLUME (IN**3) = 1.324760 TOTAL PROJECTED AREA (IN**2) = 6.3257 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000854 MOMENT OF INERTIA (Kg-M**2) = 0.000096 STATIC MOMENT, ONE SIDE (IN-LB) = 0.063864 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) = 19445.92 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.