11x14 (11x14.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 0.1125 0.0000 0.0000 0.5000 0.0000 0.4225 0.0000 0.4225 0.0000 0.1000 0.0000 0.0000 0.1650 0.9475 1.7580 0.0225 -0.7899 0.4926 0.0089 0.3949 1.2407 0.3741 0.3806 0.1075 0.0141 -0.1210 0.3300 0.8930 3.2998 0.1764 -1.5270 0.4869 0.0329 0.3688 4.8617 0.3293 0.3679 0.1275 0.0373 -0.1124 0.4950 0.8446 4.7378 0.5843 -2.0022 0.4830 0.0680 0.3441 10.6391 0.2906 0.3464 0.1563 0.0632 -0.0971 0.6600 0.8107 6.0721 1.3572 -2.0148 0.4809 0.1105 0.3209 18.1226 0.2602 0.3185 0.1911 0.0908 -0.0769 0.8250 0.7973 7.3027 2.5813 -1.3906 0.4807 0.1567 0.2992 26.4721 0.2385 0.2873 0.2291 0.1190 -0.0536 0.9900 0.8042 8.4296 4.2895 -0.0167 0.4825 0.2029 0.2789 34.5898 0.2243 0.2551 0.2671 0.1466 -0.0291 1.1550 0.8251 9.4527 6.4175 2.0966 0.4862 0.2453 0.2602 41.4866 0.2147 0.2241 0.3019 0.1726 -0.0050 1.3200 0.8494 10.3721 8.7508 4.7336 0.4920 0.2802 0.2428 46.5359 0.2063 0.1955 0.3300 0.1958 0.0170 1.4850 0.8654 11.1878 10.8894 7.4041 0.4999 0.3039 0.2270 49.4086 0.1964 0.1703 0.3477 0.2153 0.0354 1.6500 0.8632 11.8997 12.2772 9.3535 0.5099 0.3128 0.2126 49.8212 0.1835 0.1485 0.3514 0.2301 0.0487 1.8125 0.8499 12.4996 12.9051 10.4367 0.5213 0.3102 0.1999 48.5725 0.1699 0.1305 0.3447 0.2411 0.0567 1.9326 0.8434 12.8781 13.2975 11.1607 0.5298 0.3068 0.1914 47.5989 0.1614 0.1197 0.3388 0.2480 0.0601 2.0502 0.8396 13.1955 13.6271 11.8021 0.5382 0.3023 0.1838 46.6109 0.1543 0.1109 0.3322 0.2537 0.0617 2.1678 0.8378 13.4603 13.9030 12.3690 0.5463 0.2966 0.1770 45.5881 0.1483 0.1035 0.3249 0.2584 0.0616 2.2853 0.8377 13.6724 14.1253 12.8550 0.5541 0.2898 0.1709 44.5295 0.1432 0.0974 0.3168 0.2620 0.0601 2.4029 0.8390 13.8319 14.2946 13.2547 0.5614 0.2820 0.1656 43.4342 0.1389 0.0925 0.3080 0.2646 0.0573 2.5205 0.8413 13.9386 14.4112 13.5635 0.5680 0.2731 0.1610 42.3014 0.1354 0.0885 0.2984 0.2660 0.0536 2.6381 0.8442 13.9927 14.4754 13.7782 0.5738 0.2632 0.1571 41.1303 0.1327 0.0854 0.2881 0.2664 0.0489 2.7557 0.8474 14.0000 14.4936 13.9023 0.5786 0.2522 0.1541 39.9319 0.1305 0.0832 0.2770 0.2659 0.0433 2.8733 0.8504 14.0000 14.5062 13.9738 0.5824 0.2403 0.1517 38.7825 0.1290 0.0817 0.2651 0.2646 0.0368 2.9909 0.8529 14.0000 14.5209 13.9999 0.5848 0.2274 0.1501 37.6936 0.1280 0.0810 0.2525 0.2626 0.0291 3.1084 0.8545 14.0000 14.5367 14.0002 0.5859 0.2136 0.1489 36.6600 0.1272 0.0805 0.2391 0.2599 0.0206 3.2260 0.8549 14.0000 14.5521 14.0005 0.5853 0.1991 0.1477 35.6753 0.1263 0.0798 0.2249 0.2563 0.0114 3.3436 0.8536 14.0000 14.5669 14.0008 0.5831 0.1839 0.1466 34.7367 0.1251 0.0788 0.2100 0.2518 0.0016 3.4612 0.8504 14.0000 14.5812 14.0009 0.5789 0.1680 0.1454 33.8411 0.1236 0.0775 0.1943 0.2464 -0.0086 3.5788 0.8448 14.0000 14.5949 14.0008 0.5727 0.1514 0.1442 32.9860 0.1218 0.0758 0.1778 0.2401 -0.0193 3.6964 0.8364 14.0000 14.6079 14.0008 0.5643 0.1342 0.1430 32.1687 0.1196 0.0737 0.1606 0.2329 -0.0304 3.8140 0.8249 14.0000 14.6200 14.0007 0.5536 0.1163 0.1419 31.3868 0.1170 0.0711 0.1426 0.2248 -0.0419 3.9316 0.8098 14.0000 14.6313 14.0007 0.5404 0.0978 0.1407 30.6381 0.1139 0.0679 0.1239 0.2158 -0.0535 4.0491 0.7909 14.0000 14.6416 14.0006 0.5245 0.0787 0.1395 29.9205 0.1103 0.0642 0.1043 0.2059 -0.0655 4.1667 0.7676 14.0000 14.6507 14.0006 0.5058 0.0589 0.1383 29.2317 0.1062 0.0600 0.0840 0.1950 -0.0776 4.2843 0.7397 14.0000 14.6583 14.0005 0.4842 0.0386 0.1372 28.5697 0.1015 0.0552 0.0629 0.1832 -0.0898 4.4019 0.7068 14.0000 14.6643 14.0004 0.4594 0.0177 0.1360 27.9326 0.0961 0.0500 0.0411 0.1705 -0.1021 4.5195 0.6684 13.9752 14.6431 13.9756 0.4314 -0.0038 0.1348 27.2783 0.0901 0.0444 0.0185 0.1569 -0.1144 4.6371 0.6243 13.9024 14.5706 13.9027 0.4000 -0.0259 0.1336 26.5694 0.0834 0.0384 -0.0049 0.1422 -0.1264 4.7547 0.5739 13.7816 14.4459 13.7819 0.3650 -0.0486 0.1325 25.8064 0.0760 0.0322 -0.0291 0.1266 -0.1382 4.8722 0.5170 13.6128 14.2676 13.6130 0.3262 -0.0718 0.1313 24.9883 0.0679 0.0260 -0.0540 0.1101 -0.1500 4.9898 0.4532 13.3960 14.0326 13.3962 0.2836 -0.0955 0.1301 24.1125 0.0590 0.0198 -0.0797 0.0928 -0.1617 5.1074 0.3820 13.1312 13.7356 13.1314 0.2370 -0.1197 0.1289 23.1720 0.0492 0.0140 -0.1062 0.0747 -0.1734 5.2203 0.3063 12.8318 13.3803 12.8319 0.1882 -0.1434 0.1278 22.1922 0.0392 0.0090 -0.1323 0.0566 -0.1849 5.2528 0.2832 12.7375 13.2621 12.7376 0.1735 -0.1503 0.1275 21.8918 0.0361 0.0077 -0.1400 0.0513 -0.1882 5.2806 0.2630 12.6539 13.1537 12.6540 0.1606 -0.1562 0.1272 21.6259 0.0334 0.0067 -0.1465 0.0467 -0.1911 5.3083 0.2423 12.5677 13.0375 12.5677 0.1475 -0.1621 0.1269 21.3501 0.0307 0.0057 -0.1532 0.0421 -0.1939 5.3361 0.2211 12.4787 12.9118 12.4788 0.1341 -0.1680 0.1266 21.0620 0.0280 0.0047 -0.1599 0.0375 -0.1969 5.3639 0.1994 12.3871 12.7741 12.3871 0.1205 -0.1740 0.1264 20.7581 0.0252 0.0039 -0.1666 0.0328 -0.1998 5.3917 0.1773 12.2928 12.6207 12.2928 0.1066 -0.1800 0.1261 20.4327 0.0223 0.0031 -0.1733 0.0281 -0.2027 5.4194 0.1546 12.1958 12.4455 12.1958 0.0925 -0.1860 0.1258 20.0769 0.0195 0.0023 -0.1801 0.0234 -0.2057 5.4472 0.1303 12.0962 12.2379 12.0962 0.0769 -0.1924 0.1255 19.6751 0.0164 0.0017 -0.1874 0.0181 -0.2090 5.4750 0.0911 11.9938 11.9771 12.1241 0.0475 -0.2035 0.1253 19.1965 0.0114 0.0008 -0.2001 0.0056 -0.2152 5.5000 0.0043 11.8994 11.8995 11.8993 -0.0276 -0.2296 0.1250 19.0005 0.0005 0.0000 -0.2296 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.65 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.088828 TOTAL WEIGHT (Kg) = 0.040285 TOTAL VOLUME (IN**3) = 1.447115 TOTAL PROJECTED AREA (IN**2) = 6.8683 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000937 MOMENT OF INERTIA (Kg-M**2) = 0.000106 STATIC MOMENT, ONE SIDE (IN-LB) = 0.068384 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 = 82.335 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19213.26 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.