14x11 (14x11.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 1.1500 -3.0450 0.0000 0.0000 0.5750 0.0000 0.4174 0.0000 0.4800 0.0000 0.1000 0.0000 0.0000 0.1650 1.0986 -1.3505 0.0193 -0.6918 0.5686 0.0083 0.4163 1.0647 0.4574 0.4491 0.1093 0.0140 -0.1227 0.3300 1.0466 0.2352 0.1502 -1.3338 0.5658 0.0306 0.4131 4.1422 0.4324 0.4483 0.1344 0.0385 -0.1131 0.4950 1.0010 1.7119 0.4915 -1.7445 0.5660 0.0634 0.4078 8.9795 0.4082 0.4414 0.1712 0.0652 -0.0948 0.6600 0.9687 3.0798 1.1244 -1.7501 0.5688 0.1031 0.4004 15.1709 0.3878 0.4275 0.2153 0.0930 -0.0701 0.8250 0.9546 4.3388 2.1018 -1.2227 0.5738 0.1464 0.3908 22.0712 0.3730 0.4085 0.2626 0.1212 -0.0419 0.9900 0.9593 5.4888 3.4293 -0.1046 0.5808 0.1897 0.3791 28.8684 0.3636 0.3863 0.3090 0.1486 -0.0131 1.1550 0.9781 6.5300 5.0420 1.5526 0.5891 0.2298 0.3652 34.7906 0.3572 0.3625 0.3502 0.1742 0.0136 1.3200 1.0029 7.4622 6.7818 3.5472 0.5985 0.2632 0.3493 39.2726 0.3503 0.3385 0.3821 0.1966 0.0360 1.4850 1.0242 8.2856 8.3889 5.5044 0.6085 0.2865 0.3312 41.9580 0.3392 0.3150 0.4009 0.2149 0.0519 1.6500 1.0334 9.0000 9.5229 6.8981 0.6187 0.2964 0.3115 42.5693 0.3219 0.2922 0.4028 0.2282 0.0594 1.8151 1.0339 9.6059 10.1702 7.6721 0.6293 0.2958 0.2928 41.7257 0.3027 0.2707 0.3929 0.2384 0.0608 1.9817 1.0370 10.1068 10.7033 8.3710 0.6411 0.2932 0.2751 40.6823 0.2853 0.2518 0.3822 0.2476 0.0610 2.1484 1.0424 10.4969 11.1192 8.9798 0.6537 0.2888 0.2587 39.4782 0.2696 0.2352 0.3710 0.2557 0.0603 2.3152 1.0496 10.7758 11.4176 9.4865 0.6668 0.2827 0.2435 38.1282 0.2555 0.2206 0.3592 0.2629 0.0590 2.4819 1.0582 10.9435 11.5991 9.8806 0.6801 0.2752 0.2295 36.6421 0.2429 0.2077 0.3470 0.2690 0.0573 2.6486 1.0677 11.0000 11.6644 10.1537 0.6934 0.2662 0.2168 35.0271 0.2315 0.1963 0.3342 0.2740 0.0553 2.8153 1.0777 11.0000 11.6700 10.3498 0.7063 0.2560 0.2054 33.4137 0.2213 0.1863 0.3210 0.2784 0.0525 2.9821 1.0877 11.0000 11.6744 10.5201 0.7187 0.2450 0.1952 31.9257 0.2123 0.1776 0.3073 0.2826 0.0485 3.1488 1.0973 11.0000 11.6784 10.6645 0.7302 0.2330 0.1862 30.5526 0.2044 0.1700 0.2931 0.2864 0.0433 3.3155 1.1062 11.0000 11.6832 10.7832 0.7406 0.2202 0.1785 29.2849 0.1975 0.1636 0.2785 0.2898 0.0369 3.4822 1.1138 11.0000 11.6896 10.8760 0.7495 0.2064 0.1721 28.1143 0.1917 0.1583 0.2634 0.2925 0.0295 3.6490 1.1198 11.0000 11.6985 10.9431 0.7568 0.1918 0.1669 27.0329 0.1869 0.1540 0.2479 0.2945 0.0211 3.8157 1.1237 11.0000 11.7108 10.9845 0.7621 0.1762 0.1629 26.0339 0.1831 0.1507 0.2319 0.2956 0.0118 3.9824 1.1250 11.0000 11.7271 10.9999 0.7651 0.1596 0.1602 25.1110 0.1803 0.1483 0.2155 0.2959 0.0017 4.1491 1.1234 11.0000 11.7460 11.0001 0.7657 0.1425 0.1583 24.2543 0.1778 0.1460 0.1987 0.2952 -0.0090 4.3159 1.1184 11.0000 11.7641 11.0003 0.7636 0.1251 0.1563 23.4522 0.1748 0.1429 0.1815 0.2933 -0.0199 4.4826 1.1096 11.0000 11.7814 11.0004 0.7583 0.1077 0.1544 22.6996 0.1713 0.1388 0.1640 0.2902 -0.0308 4.6493 1.0964 11.0000 11.7978 11.0003 0.7498 0.0902 0.1524 21.9919 0.1671 0.1339 0.1460 0.2858 -0.0416 4.8160 1.0785 11.0000 11.8132 11.0003 0.7377 0.0726 0.1505 21.3252 0.1623 0.1279 0.1277 0.2800 -0.0525 4.9828 1.0554 11.0000 11.8275 11.0003 0.7218 0.0551 0.1486 20.6958 0.1568 0.1209 0.1090 0.2727 -0.0632 5.1495 1.0267 11.0000 11.8405 11.0002 0.7018 0.0375 0.1466 20.1004 0.1505 0.1129 0.0900 0.2638 -0.0737 5.3162 0.9919 11.0000 11.8521 11.0002 0.6774 0.0200 0.1447 19.5359 0.1435 0.1040 0.0706 0.2533 -0.0840 5.4829 0.9505 11.0000 11.8619 11.0002 0.6484 0.0025 0.1427 18.9995 0.1357 0.0943 0.0509 0.2410 -0.0940 5.6497 0.9022 11.0000 11.8696 11.0001 0.6144 -0.0149 0.1408 18.4887 0.1270 0.0838 0.0309 0.2269 -0.1038 5.8164 0.8464 11.0000 11.8748 11.0001 0.5753 -0.0322 0.1388 18.0007 0.1175 0.0728 0.0106 0.2110 -0.1132 5.9831 0.7827 11.0000 11.8766 11.0001 0.5307 -0.0494 0.1369 17.5328 0.1071 0.0615 -0.0100 0.1930 -0.1222 6.1498 0.7107 10.9630 11.8368 10.9630 0.4805 -0.0666 0.1349 17.0314 0.0959 0.0500 -0.0309 0.1730 -0.1306 6.3166 0.6299 10.8347 11.6987 10.8347 0.4243 -0.0837 0.1330 16.4237 0.0838 0.0388 -0.0521 0.1508 -0.1382 6.4833 0.5398 10.6146 11.4583 10.6147 0.3618 -0.1007 0.1310 15.7104 0.0707 0.0282 -0.0735 0.1263 -0.1452 6.6431 0.4444 10.3175 11.1244 10.3175 0.2959 -0.1169 0.1292 14.9233 0.0574 0.0189 -0.0942 0.1008 -0.1515 6.6854 0.4177 10.2250 11.0176 10.2250 0.2774 -0.1211 0.1287 14.6971 0.0538 0.0167 -0.0998 0.0937 -0.1531 6.7207 0.3948 10.1430 10.9216 10.1430 0.2616 -0.1246 0.1283 14.5011 0.0506 0.0149 -0.1044 0.0876 -0.1544 6.7561 0.3715 10.0568 10.8191 10.0569 0.2455 -0.1281 0.1279 14.2985 0.0475 0.0132 -0.1090 0.0815 -0.1557 6.7914 0.3476 9.9665 10.7095 9.9666 0.2291 -0.1316 0.1274 14.0888 0.0443 0.0115 -0.1137 0.0752 -0.1571 6.8268 0.3233 9.8722 10.5922 9.8722 0.2124 -0.1351 0.1270 13.8712 0.0411 0.0100 -0.1184 0.0689 -0.1584 6.8621 0.2978 9.7736 10.4664 9.7738 0.1946 -0.1387 0.1266 13.6446 0.0377 0.0084 -0.1233 0.0620 -0.1599 6.8975 0.2644 9.6710 10.3314 9.6723 0.1694 -0.1440 0.1262 13.4086 0.0334 0.0067 -0.1303 0.0512 -0.1625 6.9328 0.2176 9.5642 10.1851 9.6197 0.1312 -0.1522 0.1258 13.1603 0.0274 0.0045 -0.1408 0.0334 -0.1672 6.9682 0.1380 9.4533 10.0246 9.7801 0.0611 -0.1673 0.1254 12.8964 0.0173 0.0018 -0.1601 -0.0018 -0.1769 7.0000 0.0098 9.3500 9.3500 9.3499 -0.0570 -0.1930 0.1250 12.0016 0.0012 0.0000 -0.1930 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.65 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.168045 TOTAL WEIGHT (Kg) = 0.076211 TOTAL VOLUME (IN**3) = 2.737665 TOTAL PROJECTED AREA (IN**2) = 11.9659 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003412 MOMENT OF INERTIA (Kg-M**2) = 0.000385 STATIC MOMENT, ONE SIDE (IN-LB) = 0.186520 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 = 86.069 INNER LIMIT (NORMALIZED BY RADIUS) = 0.082 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12225.70 BASED ON MODULUS (MILLION) = 1.60 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.