12.5x6 (125x6.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 0.3751 0.0000 0.0000 0.5000 0.0000 0.4000 0.0000 0.4000 0.0000 0.0900 0.0000 0.0000 0.1500 0.9580 1.0042 0.0144 -0.5859 0.4936 0.0046 0.3991 0.8758 0.3823 0.3259 0.0965 0.0102 -0.0969 0.3000 0.9229 1.5960 0.1108 -1.1193 0.4894 0.0172 0.3963 3.3627 0.3658 0.3276 0.1140 0.0248 -0.0913 0.4500 0.8974 2.1506 0.3545 -1.4518 0.4872 0.0353 0.3917 7.1468 0.3515 0.3261 0.1393 0.0391 -0.0809 0.6000 0.8838 2.6678 0.7873 -1.4569 0.4869 0.0572 0.3852 11.7964 0.3405 0.3199 0.1693 0.0529 -0.0668 0.7500 0.8828 3.1477 1.4205 -1.0700 0.4883 0.0807 0.3769 16.7751 0.3328 0.3103 0.2010 0.0661 -0.0502 0.9000 0.8931 3.5904 2.2298 -0.2963 0.4914 0.1038 0.3668 21.5199 0.3276 0.2982 0.2314 0.0784 -0.0326 1.0500 0.9108 3.9957 3.1525 0.7812 0.4959 0.1247 0.3548 25.5406 0.3231 0.2843 0.2575 0.0899 -0.0155 1.2000 0.9307 4.3637 4.0888 2.0007 0.5018 0.1412 0.3409 28.4706 0.3173 0.2691 0.2763 0.1005 -0.0007 1.3500 0.9469 4.6945 4.9057 3.1282 0.5090 0.1514 0.3253 30.0429 0.3080 0.2530 0.2850 0.1099 0.0101 1.5000 0.9545 4.9879 5.4454 3.8702 0.5172 0.1534 0.3077 30.0181 0.2937 0.2363 0.2808 0.1183 0.0147 1.6499 0.9565 5.2438 5.7286 4.2306 0.5265 0.1490 0.2897 28.9254 0.2771 0.2202 0.2676 0.1258 0.0142 1.7978 0.9605 5.4600 5.9654 4.5557 0.5364 0.1434 0.2730 27.8379 0.2622 0.2063 0.2543 0.1330 0.0124 1.9457 0.9663 5.6397 6.1618 4.8491 0.5469 0.1367 0.2575 26.7494 0.2488 0.1942 0.2408 0.1399 0.0095 2.0935 0.9735 5.7832 6.3186 5.1073 0.5577 0.1290 0.2431 25.6574 0.2367 0.1835 0.2272 0.1465 0.0057 2.2414 0.9818 5.8904 6.4363 5.3269 0.5687 0.1204 0.2298 24.5616 0.2257 0.1741 0.2133 0.1526 0.0012 2.3892 0.9909 5.9614 6.5155 5.5049 0.5796 0.1108 0.2177 23.4618 0.2157 0.1658 0.1993 0.1582 -0.0040 2.5371 1.0002 5.9962 6.5568 5.6387 0.5902 0.1003 0.2067 22.3584 0.2067 0.1584 0.1851 0.1634 -0.0098 2.6849 1.0095 6.0000 6.5663 5.7314 0.6003 0.0890 0.1968 21.2676 0.1987 0.1520 0.1707 0.1680 -0.0162 2.8328 1.0184 6.0000 6.5718 5.8077 0.6097 0.0771 0.1880 20.2656 0.1915 0.1463 0.1561 0.1722 -0.0235 2.9806 1.0264 6.0000 6.5779 5.8713 0.6181 0.0646 0.1804 19.3533 0.1852 0.1414 0.1413 0.1760 -0.0317 3.1284 1.0333 6.0000 6.5852 5.9222 0.6253 0.0514 0.1739 18.5214 0.1797 0.1372 0.1263 0.1792 -0.0407 3.2763 1.0386 6.0000 6.5943 5.9603 0.6311 0.0376 0.1685 17.7621 0.1750 0.1336 0.1112 0.1819 -0.0505 3.4241 1.0419 6.0000 6.6058 5.9857 0.6353 0.0232 0.1643 17.0687 0.1711 0.1306 0.0958 0.1838 -0.0610 3.5720 1.0429 6.0000 6.6204 5.9985 0.6376 0.0081 0.1611 16.4352 0.1681 0.1282 0.0803 0.1850 -0.0721 3.7198 1.0412 6.0000 6.6381 6.0000 0.6379 -0.0077 0.1590 15.8552 0.1656 0.1260 0.0646 0.1854 -0.0839 3.8677 1.0364 6.0000 6.6555 6.0000 0.6359 -0.0234 0.1570 15.3162 0.1627 0.1233 0.0486 0.1850 -0.0956 4.0155 1.0281 6.0000 6.6721 6.0000 0.6314 -0.0389 0.1550 14.8127 0.1594 0.1198 0.0325 0.1836 -0.1074 4.1634 1.0160 6.0000 6.6878 6.0000 0.6242 -0.0543 0.1530 14.3409 0.1555 0.1155 0.0162 0.1812 -0.1190 4.3112 0.9995 6.0000 6.7024 6.0000 0.6140 -0.0695 0.1511 13.8976 0.1510 0.1103 -0.0003 0.1778 -0.1304 4.4591 0.9785 6.0000 6.7160 6.0000 0.6006 -0.0845 0.1491 13.4801 0.1459 0.1044 -0.0169 0.1733 -0.1417 4.6069 0.9524 6.0000 6.7284 6.0000 0.5839 -0.0993 0.1471 13.0858 0.1401 0.0976 -0.0338 0.1676 -0.1528 4.7547 0.9209 6.0000 6.7393 6.0000 0.5636 -0.1139 0.1451 12.7123 0.1336 0.0900 -0.0509 0.1607 -0.1636 4.9026 0.8835 6.0000 6.7487 6.0000 0.5394 -0.1283 0.1431 12.3575 0.1264 0.0818 -0.0681 0.1525 -0.1742 5.0504 0.8400 6.0000 6.7562 6.0000 0.5112 -0.1424 0.1411 12.0193 0.1185 0.0729 -0.0856 0.1430 -0.1845 5.1983 0.7900 6.0000 6.7614 6.0000 0.4787 -0.1563 0.1391 11.6957 0.1099 0.0637 -0.1032 0.1320 -0.1945 5.3461 0.7329 6.0000 6.7636 6.0000 0.4418 -0.1699 0.1371 11.3845 0.1005 0.0541 -0.1211 0.1197 -0.2042 5.4940 0.6686 6.0000 6.7619 6.0000 0.4001 -0.1832 0.1352 11.0831 0.0904 0.0444 -0.1391 0.1058 -0.2135 5.6418 0.5964 6.0000 6.7547 6.0000 0.3535 -0.1963 0.1332 10.7883 0.0794 0.0349 -0.1573 0.0904 -0.2225 5.7897 0.5162 5.9886 6.7274 5.9886 0.3017 -0.2091 0.1312 10.4775 0.0677 0.0258 -0.1757 0.0733 -0.2312 5.9314 0.4313 5.8668 6.5767 5.8668 0.2470 -0.2214 0.1293 10.0079 0.0558 0.0179 -0.1935 0.0554 -0.2388 5.9691 0.4074 5.8121 6.5108 5.8121 0.2317 -0.2247 0.1288 9.8484 0.0525 0.0159 -0.1983 0.0503 -0.2407 6.0006 0.3869 5.7589 6.4467 5.7589 0.2185 -0.2274 0.1284 9.7030 0.0497 0.0143 -0.2023 0.0460 -0.2423 6.0322 0.3660 5.6992 6.3742 5.6992 0.2051 -0.2301 0.1279 9.5466 0.0468 0.0128 -0.2063 0.0417 -0.2439 6.0638 0.3447 5.6328 6.2930 5.6328 0.1914 -0.2328 0.1275 9.3790 0.0439 0.0113 -0.2103 0.0372 -0.2455 6.0953 0.3226 5.5599 6.2027 5.5599 0.1771 -0.2355 0.1271 9.1996 0.0410 0.0099 -0.2144 0.0325 -0.2471 6.1269 0.2953 5.4803 6.1032 5.4812 0.1578 -0.2390 0.1267 9.0087 0.0374 0.0083 -0.2196 0.0251 -0.2493 6.1585 0.2598 5.3941 5.9938 5.4158 0.1306 -0.2435 0.1262 8.8050 0.0328 0.0064 -0.2265 0.0134 -0.2524 6.1900 0.2111 5.3013 5.8729 5.3860 0.0904 -0.2499 0.1258 8.5868 0.0266 0.0043 -0.2360 -0.0054 -0.2569 6.2216 0.1251 5.2019 5.7399 5.5984 0.0135 -0.2614 0.1254 8.3532 0.0157 0.0015 -0.2531 -0.0442 -0.2655 6.2500 0.0105 5.1068 5.1070 5.1068 -0.0925 -0.2765 0.1250 7.4097 0.0013 0.0000 -0.2765 0.0000 0.0000 RADIUS: 6.25 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.121829 TOTAL WEIGHT (Kg) = 0.055251 TOTAL VOLUME (IN**3) = 1.984752 TOTAL PROJECTED AREA (IN**2) = 10.5429 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002102 MOMENT OF INERTIA (Kg-M**2) = 0.000237 STATIC MOMENT, ONE SIDE (IN-LB) = 0.126406 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 = 90.532 INNER LIMIT (NORMALIZED BY RADIUS) = 0.080 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 17681.58 BASED ON MODULUS (MILLION) = 2.80 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.