10x6 (10x6.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 0.3760 0.0000 0.0000 0.5000 0.0000 0.4166 0.0000 0.4166 0.0000 0.2250 0.0000 0.0000 0.1200 0.9604 1.0306 0.0112 -0.2930 0.4940 0.0080 0.3965 0.8506 0.3808 0.3413 0.2289 0.0146 0.0149 0.2400 0.9164 1.6448 0.0868 -0.5647 0.4884 0.0297 0.3771 3.2943 0.3456 0.3324 0.2392 0.0320 0.0190 0.3600 0.8729 2.2184 0.2832 -0.7351 0.4835 0.0612 0.3585 7.1361 0.3130 0.3154 0.2538 0.0520 0.0265 0.4800 0.8351 2.7516 0.6471 -0.7224 0.4795 0.0994 0.3407 12.1093 0.2845 0.2913 0.2710 0.0739 0.0369 0.6000 0.8069 3.2442 1.2099 -0.4659 0.4766 0.1406 0.3237 17.7936 0.2612 0.2633 0.2893 0.0965 0.0493 0.7200 0.7900 3.6964 1.9769 0.0643 0.4750 0.1817 0.3074 23.6046 0.2428 0.2345 0.3072 0.1187 0.0629 0.8400 0.7829 4.1081 2.9107 0.8469 0.4750 0.2193 0.2919 28.8767 0.2285 0.2070 0.3231 0.1397 0.0767 0.9600 0.7817 4.4793 3.9147 1.7857 0.4768 0.2500 0.2771 32.9838 0.2166 0.1827 0.3353 0.1585 0.0896 1.0800 0.7811 4.8100 4.8221 2.6913 0.4805 0.2705 0.2632 35.3980 0.2056 0.1626 0.3418 0.1740 0.1005 1.2000 0.7764 5.1002 5.4072 3.2878 0.4866 0.2775 0.2500 35.6463 0.1941 0.1478 0.3404 0.1854 0.1077 1.3199 0.7695 5.3497 5.6758 3.5646 0.4943 0.2744 0.2376 34.3873 0.1828 0.1369 0.3332 0.1936 0.1114 1.4383 0.7661 5.5564 5.8962 3.8376 0.5028 0.2703 0.2261 33.1226 0.1732 0.1278 0.3256 0.2008 0.1138 1.5566 0.7659 5.7235 6.0749 4.1084 0.5118 0.2652 0.2154 31.8466 0.1649 0.1198 0.3177 0.2073 0.1150 1.6748 0.7682 5.8513 6.2125 4.3713 0.5211 0.2593 0.2054 30.5559 0.1578 0.1128 0.3093 0.2129 0.1153 1.7931 0.7728 5.9398 6.3092 4.6192 0.5306 0.2524 0.1962 29.2490 0.1516 0.1066 0.3006 0.2177 0.1148 1.9114 0.7793 5.9889 6.3655 4.8447 0.5399 0.2448 0.1877 27.9251 0.1463 0.1012 0.2916 0.2215 0.1136 2.0297 0.7871 6.0000 6.3828 5.0409 0.5490 0.2364 0.1800 26.5882 0.1417 0.0963 0.2821 0.2244 0.1117 2.1479 0.7959 6.0000 6.3889 5.2232 0.5575 0.2274 0.1730 25.3326 0.1377 0.0920 0.2723 0.2266 0.1088 2.2662 0.8053 6.0000 6.3951 5.3964 0.5654 0.2178 0.1668 24.1861 0.1343 0.0883 0.2621 0.2280 0.1048 2.3845 0.8148 6.0000 6.4018 5.5559 0.5722 0.2077 0.1613 23.1368 0.1314 0.0852 0.2515 0.2287 0.0999 2.5028 0.8240 6.0000 6.4093 5.6976 0.5780 0.1970 0.1566 22.1747 0.1290 0.0825 0.2406 0.2286 0.0940 2.6210 0.8324 6.0000 6.4178 5.8171 0.5824 0.1858 0.1526 21.2910 0.1271 0.0804 0.2293 0.2277 0.0872 2.7393 0.8398 6.0000 6.4276 5.9100 0.5851 0.1740 0.1494 20.4781 0.1255 0.0787 0.2176 0.2259 0.0796 2.8576 0.8455 6.0000 6.4391 5.9722 0.5862 0.1617 0.1470 19.7293 0.1243 0.0776 0.2056 0.2232 0.0713 2.9759 0.8493 6.0000 6.4524 5.9992 0.5852 0.1488 0.1453 19.0389 0.1234 0.0770 0.1933 0.2196 0.0621 3.0941 0.8506 6.0000 6.4670 6.0000 0.5820 0.1355 0.1441 18.3996 0.1225 0.0766 0.1806 0.2151 0.0525 3.2124 0.8491 6.0000 6.4813 6.0001 0.5764 0.1221 0.1429 17.8021 0.1213 0.0757 0.1675 0.2094 0.0427 3.3307 0.8443 6.0000 6.4950 6.0001 0.5681 0.1085 0.1417 17.2422 0.1196 0.0742 0.1541 0.2026 0.0328 3.4490 0.8358 6.0000 6.5081 6.0001 0.5571 0.0948 0.1405 16.7161 0.1174 0.0721 0.1404 0.1947 0.0229 3.5672 0.8232 6.0000 6.5206 6.0001 0.5429 0.0811 0.1393 16.2207 0.1147 0.0693 0.1263 0.1855 0.0131 3.6855 0.8060 6.0000 6.5322 6.0001 0.5255 0.0674 0.1381 15.7530 0.1113 0.0659 0.1119 0.1750 0.0033 3.8038 0.7837 6.0000 6.5429 6.0001 0.5046 0.0537 0.1370 15.3103 0.1073 0.0618 0.0971 0.1633 -0.0064 3.9221 0.7561 6.0000 6.5524 6.0000 0.4801 0.0399 0.1358 14.8901 0.1027 0.0570 0.0821 0.1503 -0.0159 4.0403 0.7226 6.0000 6.5606 6.0000 0.4516 0.0263 0.1346 14.4900 0.0973 0.0517 0.0667 0.1360 -0.0253 4.1586 0.6828 6.0000 6.5669 6.0000 0.4190 0.0127 0.1334 14.1076 0.0911 0.0458 0.0509 0.1203 -0.0344 4.2769 0.6363 5.9988 6.5706 5.9977 0.3821 -0.0008 0.1322 13.7397 0.0841 0.0394 0.0349 0.1033 -0.0433 4.3952 0.5827 5.9663 6.5696 5.9362 0.3406 -0.0137 0.1310 13.3815 0.0764 0.0328 0.0186 0.0847 -0.0518 4.5134 0.5218 5.8889 6.5813 5.8086 0.2944 -0.0255 0.1299 13.0654 0.0678 0.0261 0.0024 0.0648 -0.0599 4.6317 0.4531 5.7669 6.6269 5.6386 0.2433 -0.0364 0.1287 12.8282 0.0583 0.0195 -0.0137 0.0433 -0.0673 4.7451 0.3793 5.6077 6.7170 5.4588 0.1893 -0.0465 0.1275 12.6963 0.0484 0.0136 -0.0290 0.0213 -0.0739 4.7753 0.3583 5.5586 6.7492 5.4110 0.1742 -0.0492 0.1272 12.6773 0.0456 0.0121 -0.0330 0.0153 -0.0755 4.8005 0.3403 5.5151 6.7785 5.3716 0.1612 -0.0514 0.1270 12.6659 0.0432 0.0109 -0.0365 0.0101 -0.0769 4.8258 0.3218 5.4696 6.8169 5.3317 0.1480 -0.0537 0.1267 12.6708 0.0408 0.0097 -0.0399 0.0049 -0.0782 4.8510 0.3029 5.4221 6.8504 5.2940 0.1346 -0.0560 0.1265 12.6668 0.0383 0.0086 -0.0434 -0.0004 -0.0796 4.8763 0.2825 5.3725 6.8847 5.2577 0.1198 -0.0587 0.1262 12.6644 0.0357 0.0075 -0.0473 -0.0063 -0.0811 4.9015 0.2570 5.3208 6.9192 5.2276 0.1003 -0.0625 0.1260 12.6624 0.0324 0.0062 -0.0524 -0.0147 -0.0833 4.9268 0.2245 5.2672 6.9523 5.2352 0.0740 -0.0678 0.1257 12.6580 0.0282 0.0047 -0.0592 -0.0268 -0.0864 4.9520 0.1800 5.2115 6.9815 5.3201 0.0363 -0.0757 0.1255 12.6466 0.0226 0.0031 -0.0690 -0.0451 -0.0910 4.9773 0.1016 5.1537 7.0045 5.9008 -0.0343 -0.0910 0.1252 12.6246 0.0127 0.0010 -0.0874 -0.0811 -0.1000 5.0000 0.0090 5.1000 5.1000 5.1000 -0.1191 -0.1101 0.1250 9.2209 0.0011 0.0000 -0.1101 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) = 0.071560 TOTAL WEIGHT (Kg) = 0.032453 TOTAL VOLUME (IN**3) = 1.165798 TOTAL PROJECTED AREA (IN**2) = 6.9801 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000709 MOMENT OF INERTIA (Kg-M**2) = 0.000080 STATIC MOMENT, ONE SIDE (IN-LB) = 0.053617 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) = 21619.20 BASED ON MODULUS (MILLION) = 2.86 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.