13.5x10 (135x10.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 1.0840 0.6250 0.0000 0.0000 0.5420 0.0000 0.4435 0.0000 0.4807 0.0000 0.0500 0.0000 0.0000 0.1680 1.0326 1.8427 0.0206 -1.0130 0.5332 0.0051 0.4197 1.1202 0.4334 0.4874 0.0561 0.0095 -0.2075 0.3360 0.9826 2.9757 0.1608 -1.9577 0.5238 0.0188 0.3969 4.3560 0.3900 0.4729 0.0724 0.0269 -0.2020 0.5040 0.9407 4.0240 0.5258 -2.6055 0.5147 0.0386 0.3751 9.4273 0.3528 0.4487 0.0958 0.0448 -0.1918 0.6720 0.9135 4.9876 1.1990 -2.7518 0.5062 0.0620 0.3542 15.8526 0.3236 0.4174 0.1236 0.0626 -0.1782 0.8400 0.9054 5.8666 2.2279 -2.2552 0.4989 0.0867 0.3344 22.8856 0.3028 0.3826 0.1528 0.0798 -0.1624 1.0080 0.9156 6.6609 3.6038 -1.0713 0.4933 0.1106 0.3156 29.6405 0.2889 0.3475 0.1808 0.0960 -0.1461 1.1760 0.9385 7.3705 5.2381 0.7008 0.4901 0.1311 0.2977 35.3331 0.2794 0.3143 0.2044 0.1108 -0.1306 1.3440 0.9652 7.9955 6.9440 2.7776 0.4897 0.1461 0.2808 39.4304 0.2710 0.2848 0.2208 0.1239 -0.1177 1.5120 0.9859 8.5358 8.4363 4.6794 0.4927 0.1531 0.2649 41.6057 0.2612 0.2604 0.2269 0.1349 -0.1094 1.6800 0.9926 8.9914 9.3636 5.7751 0.4996 0.1500 0.2500 41.5751 0.2481 0.2419 0.2200 0.1437 -0.1082 1.8474 0.9897 9.3613 9.7600 6.1609 0.5094 0.1397 0.2361 40.0575 0.2336 0.2241 0.2028 0.1511 -0.1123 2.0054 0.9891 9.6331 10.0489 6.6523 0.5194 0.1295 0.2239 38.5728 0.2214 0.2016 0.1844 0.1580 -0.1162 2.1628 0.9903 9.8294 10.2589 7.2036 0.5299 0.1190 0.2126 37.0501 0.2105 0.1780 0.1655 0.1638 -0.1200 2.3202 0.9930 9.9515 10.3916 7.7315 0.5406 0.1081 0.2021 35.4819 0.2007 0.1574 0.1478 0.1679 -0.1233 2.4776 0.9968 9.9992 10.4476 8.1628 0.5515 0.0968 0.1926 33.8667 0.1920 0.1426 0.1321 0.1703 -0.1260 2.6350 1.0013 10.0000 10.4550 8.4592 0.5622 0.0853 0.1839 32.2719 0.1841 0.1343 0.1190 0.1718 -0.1276 2.7924 1.0062 10.0000 10.4603 8.6851 0.5726 0.0736 0.1760 30.8033 0.1771 0.1304 0.1078 0.1733 -0.1287 2.9498 1.0112 10.0000 10.4655 8.9129 0.5824 0.0617 0.1691 29.4520 0.1709 0.1270 0.0970 0.1751 -0.1302 3.1072 1.0158 10.0000 10.4720 9.1444 0.5915 0.0494 0.1629 28.2090 0.1655 0.1239 0.0862 0.1772 -0.1323 3.2646 1.0198 10.0000 10.4797 9.3732 0.5996 0.0367 0.1577 27.0628 0.1608 0.1211 0.0753 0.1791 -0.1352 3.4220 1.0227 10.0000 10.4889 9.5974 0.6066 0.0235 0.1533 26.0047 0.1568 0.1188 0.0641 0.1805 -0.1390 3.5794 1.0242 10.0000 10.5001 9.7889 0.6122 0.0099 0.1498 25.0271 0.1534 0.1166 0.0523 0.1818 -0.1440 3.7368 1.0239 10.0000 10.5138 9.9286 0.6163 -0.0043 0.1471 24.1229 0.1507 0.1147 0.0396 0.1829 -0.1503 3.8942 1.0215 10.0000 10.5304 9.9967 0.6185 -0.0191 0.1453 23.2860 0.1485 0.1128 0.0259 0.1839 -0.1580 4.0516 1.0166 10.0000 10.5489 10.0004 0.6188 -0.0345 0.1442 22.5085 0.1466 0.1107 0.0110 0.1847 -0.1671 4.2089 1.0089 10.0000 10.5669 10.0004 0.6169 -0.0501 0.1431 21.7802 0.1443 0.1082 -0.0043 0.1847 -0.1766 4.3663 0.9979 10.0000 10.5839 10.0003 0.6126 -0.0660 0.1419 21.0959 0.1416 0.1050 -0.0201 0.1839 -0.1863 4.5237 0.9832 10.0000 10.5998 10.0003 0.6057 -0.0821 0.1408 20.4516 0.1385 0.1011 -0.0364 0.1821 -0.1963 4.6811 0.9646 10.0000 10.6144 10.0003 0.5960 -0.0987 0.1397 19.8435 0.1348 0.0965 -0.0533 0.1793 -0.2066 4.8385 0.9416 10.0000 10.6275 10.0003 0.5833 -0.1155 0.1386 19.2682 0.1305 0.0913 -0.0708 0.1755 -0.2172 4.9959 0.9138 10.0000 10.6387 10.0003 0.5673 -0.1328 0.1375 18.7224 0.1256 0.0853 -0.0890 0.1706 -0.2281 5.1533 0.8810 10.0000 10.6478 10.0003 0.5480 -0.1505 0.1363 18.2032 0.1201 0.0787 -0.1080 0.1646 -0.2393 5.3107 0.8426 10.0000 10.6540 10.0002 0.5249 -0.1686 0.1352 17.7076 0.1139 0.0715 -0.1277 0.1573 -0.2509 5.4681 0.7984 10.0000 10.6568 10.0002 0.4981 -0.1872 0.1341 17.2327 0.1071 0.0637 -0.1483 0.1488 -0.2628 5.6255 0.7480 10.0000 10.6549 10.0002 0.4672 -0.2064 0.1330 16.7752 0.0995 0.0555 -0.1697 0.1390 -0.2751 5.7829 0.6909 9.9984 10.6452 9.9986 0.4320 -0.2262 0.1319 16.3292 0.0911 0.0471 -0.1922 0.1279 -0.2878 5.9403 0.6269 9.9457 10.5754 9.9458 0.3924 -0.2466 0.1308 15.8196 0.0820 0.0386 -0.2156 0.1153 -0.3007 6.0977 0.5555 9.8186 10.4179 9.8188 0.3481 -0.2678 0.1296 15.2118 0.0720 0.0302 -0.2400 0.1012 -0.3138 6.2551 0.4764 9.6173 10.1645 9.6174 0.2990 -0.2897 0.1285 14.5005 0.0612 0.0222 -0.2656 0.0856 -0.3273 6.4061 0.3928 9.3544 9.8156 9.3545 0.2470 -0.3114 0.1274 13.7047 0.0501 0.0151 -0.2911 0.0692 -0.3408 6.4466 0.3691 9.2721 9.7004 9.2722 0.2323 -0.3174 0.1272 13.4679 0.0469 0.0134 -0.2982 0.0646 -0.3445 6.4807 0.3487 9.1992 9.5950 9.1992 0.2196 -0.3224 0.1269 13.2592 0.0443 0.0119 -0.3042 0.0606 -0.3477 6.5148 0.3279 9.1227 9.4809 9.1227 0.2067 -0.3274 0.1267 13.0407 0.0415 0.0106 -0.3102 0.0566 -0.3509 6.5489 0.3067 9.0427 9.3569 9.0428 0.1935 -0.3325 0.1264 12.8110 0.0388 0.0093 -0.3163 0.0525 -0.3541 6.5830 0.2851 8.9593 9.2212 8.9593 0.1800 -0.3376 0.1262 12.5680 0.0360 0.0081 -0.3225 0.0484 -0.3574 6.6170 0.2617 8.8723 9.0718 8.8725 0.1650 -0.3430 0.1259 12.3089 0.0330 0.0068 -0.3291 0.0435 -0.3610 6.6511 0.2346 8.7819 8.9055 8.7823 0.1465 -0.3491 0.1257 12.0298 0.0295 0.0055 -0.3366 0.0368 -0.3650 6.6852 0.2009 8.6880 8.7174 8.7525 0.1217 -0.3565 0.1255 11.7244 0.0252 0.0041 -0.3457 0.0268 -0.3699 6.7193 0.1534 8.5906 8.5002 8.8864 0.0835 -0.3663 0.1252 11.3836 0.0192 0.0024 -0.3581 0.0099 -0.3766 6.7500 0.0327 8.5000 8.5000 8.5000 -0.0044 -0.3851 0.1250 11.3329 0.0041 0.0000 -0.3851 0.0000 0.0000 RADIUS: 6.75 PROPELLER RADIUS (IN) HUBRAD: 0.54 HUB RADIUS (IN) HUBTRA: 1.68 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.140803 TOTAL WEIGHT (Kg) = 0.063856 TOTAL VOLUME (IN**3) = 2.293868 TOTAL PROJECTED AREA (IN**2) = 10.7539 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002366 MOMENT OF INERTIA (Kg-M**2) = 0.000267 STATIC MOMENT, ONE SIDE (IN-LB) = 0.137704 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 = 80.091 INNER LIMIT (NORMALIZED BY RADIUS) = 0.080 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14191.46 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.