10x3 (10x3.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 3.0000 0.0000 0.0000 0.5000 0.0000 0.3144 0.0000 0.3144 0.0000 0.1250 0.0000 0.0000 0.1200 0.9638 3.0000 0.0090 -0.3952 0.4941 0.0019 0.3033 0.6804 0.2923 0.3165 0.1255 0.0093 -0.0641 0.2400 0.9282 3.0000 0.0683 -0.7545 0.4886 0.0068 0.2925 2.5941 0.2715 0.3080 0.1267 0.0223 -0.0671 0.3600 0.8956 3.0000 0.2180 -0.9885 0.4837 0.0139 0.2821 5.5040 0.2526 0.2916 0.1276 0.0368 -0.0704 0.4800 0.8679 3.0000 0.4843 -1.0189 0.4797 0.0222 0.2721 9.1221 0.2361 0.2680 0.1284 0.0527 -0.0733 0.6000 0.8464 3.0000 0.8765 -0.8017 0.4767 0.0309 0.2624 13.0893 0.2221 0.2405 0.1290 0.0695 -0.0750 0.7200 0.8308 3.0000 1.3820 -0.3331 0.4751 0.0391 0.2532 16.9877 0.2103 0.2115 0.1295 0.0871 -0.0749 0.8400 0.8193 3.0000 1.9606 0.3395 0.4751 0.0459 0.2443 20.3790 0.2002 0.1833 0.1294 0.1051 -0.0724 0.9600 0.8089 3.0000 2.5403 1.1075 0.4768 0.0504 0.2358 22.8385 0.1908 0.1577 0.1283 0.1232 -0.0675 1.0800 0.7963 3.0000 3.0149 1.7944 0.4806 0.0518 0.2277 23.9551 0.1813 0.1362 0.1254 0.1406 -0.0606 1.2000 0.7788 3.0000 3.2455 2.1558 0.4866 0.0493 0.2200 23.2893 0.1713 0.1202 0.1200 0.1557 -0.0526 1.3199 0.7602 3.0000 3.2612 2.2015 0.4943 0.0440 0.2127 21.4662 0.1617 0.1090 0.1130 0.1685 -0.0456 1.4383 0.7467 3.0000 3.2737 2.2539 0.5028 0.0386 0.2058 19.9131 0.1537 0.1002 0.1061 0.1804 -0.0409 1.5566 0.7378 3.0000 3.2855 2.3150 0.5118 0.0331 0.1993 18.5691 0.1470 0.0932 0.0992 0.1914 -0.0382 1.6748 0.7328 3.0000 3.2968 2.3825 0.5211 0.0274 0.1932 17.3951 0.1416 0.0876 0.0924 0.2013 -0.0370 1.7931 0.7314 3.0000 3.3078 2.4546 0.5306 0.0215 0.1874 16.3619 0.1371 0.0832 0.0856 0.2102 -0.0372 1.9114 0.7330 3.0000 3.3185 2.5294 0.5399 0.0153 0.1821 15.4466 0.1334 0.0798 0.0788 0.2178 -0.0384 2.0297 0.7371 3.0000 3.3291 2.6048 0.5490 0.0090 0.1770 14.6307 0.1305 0.0772 0.0719 0.2242 -0.0406 2.1479 0.7431 3.0000 3.3397 2.6789 0.5575 0.0023 0.1724 13.8994 0.1281 0.0752 0.0650 0.2294 -0.0435 2.2662 0.7507 3.0000 3.3505 2.7497 0.5654 -0.0045 0.1682 13.2409 0.1262 0.0738 0.0580 0.2333 -0.0472 2.3845 0.7593 3.0000 3.3614 2.8154 0.5722 -0.0116 0.1643 12.6453 0.1247 0.0727 0.0509 0.2360 -0.0514 2.5028 0.7683 3.0000 3.3725 2.8740 0.5780 -0.0189 0.1607 12.1044 0.1235 0.0720 0.0437 0.2374 -0.0561 2.6210 0.7772 3.0000 3.3839 2.9236 0.5824 -0.0264 0.1576 11.6115 0.1225 0.0716 0.0364 0.2375 -0.0613 2.7393 0.7856 3.0000 3.3958 2.9624 0.5851 -0.0341 0.1548 11.1609 0.1216 0.0713 0.0289 0.2363 -0.0670 2.8576 0.7930 3.0000 3.4081 2.9884 0.5862 -0.0420 0.1524 10.7478 0.1209 0.0712 0.0212 0.2340 -0.0730 2.9759 0.7988 3.0000 3.4210 2.9997 0.5852 -0.0502 0.1504 10.3682 0.1201 0.0711 0.0134 0.2303 -0.0794 3.0941 0.8025 3.0000 3.4340 3.0000 0.5820 -0.0584 0.1486 10.0172 0.1192 0.0709 0.0053 0.2255 -0.0860 3.2124 0.8036 3.0000 3.4463 3.0000 0.5764 -0.0666 0.1468 9.6894 0.1180 0.0702 -0.0030 0.2193 -0.0927 3.3307 0.8016 3.0000 3.4577 3.0001 0.5681 -0.0748 0.1450 9.3819 0.1163 0.0690 -0.0115 0.2119 -0.0993 3.4490 0.7959 3.0000 3.4681 3.0001 0.5571 -0.0829 0.1433 9.0925 0.1140 0.0672 -0.0203 0.2032 -0.1059 3.5672 0.7862 3.0000 3.4774 3.0001 0.5429 -0.0910 0.1415 8.8188 0.1112 0.0648 -0.0294 0.1932 -0.1124 3.6855 0.7718 3.0000 3.4852 3.0001 0.5255 -0.0989 0.1397 8.5591 0.1078 0.0617 -0.0389 0.1821 -0.1189 3.8038 0.7523 3.0000 3.4915 3.0001 0.5046 -0.1067 0.1379 8.3115 0.1038 0.0579 -0.0486 0.1697 -0.1252 3.9221 0.7271 3.0000 3.4959 3.0001 0.4801 -0.1145 0.1362 8.0741 0.0990 0.0534 -0.0587 0.1560 -0.1315 4.0403 0.6957 3.0000 3.4978 3.0001 0.4516 -0.1221 0.1344 7.8450 0.0935 0.0483 -0.0692 0.1412 -0.1377 4.1586 0.6577 3.0000 3.4966 3.0001 0.4190 -0.1297 0.1326 7.6220 0.0872 0.0427 -0.0800 0.1251 -0.1437 4.2769 0.6124 3.0000 3.4921 2.9990 0.3821 -0.1371 0.1308 7.4041 0.0801 0.0366 -0.0913 0.1079 -0.1496 4.3952 0.5596 3.0000 3.5092 2.9727 0.3406 -0.1438 0.1291 7.2418 0.0722 0.0302 -0.1030 0.0895 -0.1555 4.5134 0.4986 2.9997 3.5732 2.9271 0.2944 -0.1497 0.1273 7.1814 0.0635 0.0238 -0.1150 0.0699 -0.1613 4.6317 0.4290 2.9688 3.6709 2.8529 0.2433 -0.1549 0.1255 7.1893 0.0538 0.0174 -0.1271 0.0491 -0.1667 4.7451 0.3535 2.8918 3.7780 2.7588 0.1893 -0.1598 0.1238 7.2219 0.0438 0.0118 -0.1389 0.0281 -0.1714 4.7753 0.3320 2.8636 3.8067 2.7325 0.1742 -0.1611 0.1234 7.2308 0.0410 0.0104 -0.1421 0.0224 -0.1726 4.8005 0.3134 2.8375 3.8296 2.7104 0.1612 -0.1623 0.1230 7.2359 0.0386 0.0093 -0.1448 0.0176 -0.1736 4.8258 0.2944 2.8090 3.8503 2.6886 0.1480 -0.1636 0.1226 7.2369 0.0361 0.0082 -0.1475 0.0126 -0.1746 4.8510 0.2749 2.7782 3.8674 2.6672 0.1346 -0.1649 0.1222 7.2313 0.0336 0.0071 -0.1503 0.0077 -0.1756 4.8763 0.2550 2.7452 3.8788 2.6462 0.1208 -0.1664 0.1219 7.2153 0.0311 0.0061 -0.1532 0.0027 -0.1767 4.9015 0.2329 2.7098 3.8823 2.6260 0.1052 -0.1681 0.1215 7.1849 0.0283 0.0051 -0.1564 -0.0032 -0.1778 4.9268 0.2043 2.6722 3.8735 2.6518 0.0834 -0.1707 0.1211 7.1323 0.0247 0.0040 -0.1607 -0.0124 -0.1795 4.9520 0.1655 2.6322 3.8454 2.7871 0.0516 -0.1745 0.1207 7.0453 0.0200 0.0026 -0.1667 -0.0269 -0.1820 4.9773 0.0995 2.5900 3.7884 3.5737 -0.0069 -0.1817 0.1203 6.9071 0.0120 0.0010 -0.1771 -0.0555 -0.1864 5.0000 0.0075 2.5500 2.5502 2.5500 -0.0917 -0.1921 0.1200 4.6407 0.0009 0.0000 -0.1921 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) = 0.063267 TOTAL WEIGHT (Kg) = 0.028692 TOTAL VOLUME (IN**3) = 1.030695 TOTAL PROJECTED AREA (IN**2) = 7.1037 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000635 MOMENT OF INERTIA (Kg-M**2) = 0.000072 STATIC MOMENT, ONE SIDE (IN-LB) = 0.047310 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 = 90.834 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 17095.79 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.