11x5.5MR (11x55MR.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 0.6500 -10.5435 0.0000 0.0000 0.3250 0.0000 0.5065 0.0000 0.3292 0.0000 0.1350 0.0000 0.0000 0.0880 0.6389 -8.3742 0.0064 -0.2160 0.3216 0.0078 0.4542 0.6669 0.2902 0.1423 0.1393 0.0023 0.0062 0.1760 0.6251 -6.3623 0.0504 -0.4125 0.3202 0.0292 0.4065 2.6070 0.2541 0.1403 0.1513 0.0080 0.0166 0.2640 0.6118 -4.5079 0.1673 -0.5427 0.3207 0.0610 0.3632 5.7584 0.2222 0.1363 0.1689 0.0166 0.0323 0.3520 0.6028 -2.8111 0.3907 -0.5029 0.3231 0.1000 0.3241 10.0193 0.1953 0.1264 0.1902 0.0276 0.0523 0.4400 0.6017 -1.2718 0.7452 -0.2271 0.3273 0.1432 0.2889 15.0850 0.1739 0.1129 0.2137 0.0400 0.0745 0.5280 0.6116 0.1101 1.2408 0.3164 0.3334 0.1876 0.2576 20.5068 0.1575 0.0984 0.2383 0.0527 0.0971 0.6160 0.6341 1.3344 1.8674 1.1122 0.3411 0.2302 0.2298 25.7557 0.1457 0.0845 0.2631 0.0650 0.1180 0.7040 0.6694 2.4012 2.5892 2.0411 0.3505 0.2679 0.2053 30.3421 0.1374 0.0729 0.2870 0.0760 0.1353 0.7920 0.7163 3.3104 3.3462 2.9726 0.3614 0.2979 0.1838 33.9178 0.1317 0.0653 0.3084 0.0844 0.1465 0.8800 0.7735 4.0622 4.0624 3.7922 0.3738 0.3171 0.1653 36.3053 0.1279 0.0634 0.3241 0.0876 0.1475 0.9711 0.8361 4.6743 4.6743 4.4515 0.3871 0.3275 0.1489 37.4560 0.1245 0.0656 0.3339 0.0849 0.1415 1.1148 0.9239 5.2972 5.2972 5.1500 0.4057 0.3376 0.1283 37.0989 0.1185 0.0680 0.3440 0.0739 0.1373 1.2616 0.9999 5.5000 5.5000 5.4033 0.4220 0.3403 0.1128 34.7549 0.1128 0.0701 0.3477 0.0569 0.1401 1.4084 1.0620 5.5000 5.5000 5.4369 0.4354 0.3358 0.1022 31.8623 0.1085 0.0719 0.3450 0.0390 0.1439 1.5552 1.1105 5.5000 5.5000 5.4582 0.4462 0.3285 0.0952 29.3736 0.1057 0.0736 0.3395 0.0240 0.1461 1.7020 1.1453 5.5000 5.5000 5.4698 0.4543 0.3201 0.0910 27.2176 0.1042 0.0751 0.3330 0.0122 0.1485 1.8488 1.1666 5.5000 5.5000 5.4744 0.4600 0.3108 0.0884 25.3367 0.1032 0.0759 0.3257 0.0042 0.1508 1.9956 1.1745 5.5000 5.5000 5.4774 0.4631 0.3008 0.0865 23.6847 0.1016 0.0754 0.3175 -0.0003 0.1529 2.1423 1.1692 5.5000 5.5000 5.4811 0.4639 0.2902 0.0848 22.2247 0.0992 0.0734 0.3085 -0.0013 0.1546 2.2891 1.1572 5.5000 5.5000 5.4846 0.4625 0.2790 0.0833 20.9265 0.0964 0.0708 0.2988 -0.0014 0.1550 2.4359 1.1422 5.5000 5.5000 5.4876 0.4588 0.2672 0.0819 19.7659 0.0936 0.0681 0.2885 -0.0020 0.1539 2.5827 1.1244 5.5000 5.5000 5.4899 0.4530 0.2549 0.0807 18.7229 0.0908 0.0652 0.2775 -0.0030 0.1514 2.7295 1.1037 5.5000 5.5000 5.4918 0.4451 0.2422 0.0797 17.7810 0.0880 0.0621 0.2659 -0.0047 0.1478 2.8763 1.0804 5.5000 5.5000 5.4938 0.4353 0.2292 0.0788 16.9267 0.0851 0.0590 0.2538 -0.0069 0.1431 3.0231 1.0545 5.5000 5.5000 5.4960 0.4236 0.2158 0.0781 16.1486 0.0823 0.0558 0.2413 -0.0096 0.1375 3.1699 1.0261 5.5000 5.5000 5.4981 0.4101 0.2022 0.0775 15.4372 0.0795 0.0526 0.2283 -0.0130 0.1310 3.3167 0.9953 5.5000 5.5000 5.4964 0.3949 0.1882 0.0770 14.7846 0.0766 0.0496 0.2150 -0.0179 0.1232 3.4635 0.9622 5.5000 5.5000 5.4887 0.3780 0.1740 0.0766 14.1838 0.0737 0.0468 0.2013 -0.0245 0.1143 3.6103 0.9270 5.5000 5.5000 5.4748 0.3596 0.1597 0.0763 13.6290 0.0708 0.0443 0.1874 -0.0324 0.1043 3.7571 0.8897 5.5000 5.5000 5.4549 0.3397 0.1452 0.0762 13.1153 0.0678 0.0419 0.1733 -0.0412 0.0938 3.9039 0.8505 5.5000 5.5000 5.4297 0.3184 0.1308 0.0761 12.6382 0.0647 0.0395 0.1590 -0.0504 0.0828 4.0507 0.8093 5.5000 5.5000 5.4003 0.2958 0.1165 0.0761 12.1942 0.0616 0.0370 0.1446 -0.0598 0.0717 4.1974 0.7665 5.5000 5.5000 5.3685 0.2720 0.1023 0.0761 11.7799 0.0583 0.0343 0.1302 -0.0690 0.0606 4.3442 0.7219 5.5000 5.5000 5.3361 0.2470 0.0884 0.0763 11.3924 0.0550 0.0314 0.1157 -0.0779 0.0498 4.4910 0.6758 5.5000 5.5000 5.3056 0.2210 0.0748 0.0764 11.0293 0.0517 0.0283 0.1013 -0.0863 0.0393 4.6378 0.6283 5.5000 5.5000 5.2800 0.1939 0.0615 0.0766 10.6884 0.0482 0.0251 0.0871 -0.0942 0.0292 4.7846 0.5794 5.5000 5.5000 5.2623 0.1660 0.0487 0.0769 10.3677 0.0446 0.0218 0.0729 -0.1017 0.0196 4.9314 0.5293 5.5000 5.5000 5.2554 0.1372 0.0363 0.0772 10.0655 0.0409 0.0185 0.0590 -0.1089 0.0105 5.0782 0.4780 5.5000 5.5000 5.2522 0.1077 0.0245 0.0775 9.7802 0.0370 0.0153 0.0451 -0.1158 0.0016 5.2188 0.4278 5.5000 5.5000 5.1985 0.0787 0.0136 0.0778 9.5216 0.0333 0.0123 0.0307 -0.1224 -0.0081 5.2528 0.4128 5.5000 5.5000 5.1736 0.0689 0.0105 0.0779 9.4611 0.0321 0.0115 0.0265 -0.1254 -0.0109 5.2806 0.3974 5.5000 5.5000 5.1495 0.0578 0.0076 0.0779 9.4123 0.0310 0.0107 0.0226 -0.1295 -0.0136 5.3083 0.3790 5.5000 5.5000 5.1271 0.0437 0.0042 0.0780 9.3639 0.0295 0.0098 0.0180 -0.1352 -0.0166 5.3361 0.3569 5.5000 5.5000 5.1076 0.0261 0.0002 0.0780 9.3160 0.0278 0.0087 0.0127 -0.1428 -0.0200 5.3639 0.3305 5.5000 5.5000 5.0913 0.0042 -0.0044 0.0781 9.2686 0.0258 0.0075 0.0067 -0.1526 -0.0237 5.3917 0.2986 5.5000 5.5000 5.0836 -0.0232 -0.0099 0.0781 9.2217 0.0233 0.0061 -0.0002 -0.1654 -0.0280 5.4194 0.2586 5.5000 5.5000 5.0983 -0.0585 -0.0166 0.0782 9.1752 0.0202 0.0046 -0.0086 -0.1823 -0.0329 5.4472 0.2048 5.5000 5.5000 5.1820 -0.1075 -0.0254 0.0783 9.1292 0.0160 0.0029 -0.0194 -0.2065 -0.0389 5.4750 0.1145 5.5000 5.5000 5.6992 -0.1924 -0.0399 0.0783 9.0837 0.0090 0.0010 -0.0367 -0.2496 -0.0480 5.5000 0.0163 5.5000 5.5028 5.5028 -0.2857 -0.0554 0.0784 9.0476 0.0013 0.0000 -0.0554 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.88 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.039407 TOTAL WEIGHT (Kg) = 0.017871 TOTAL VOLUME (IN**3) = 0.641982 TOTAL PROJECTED AREA (IN**2) = 8.6952 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000593 MOMENT OF INERTIA (Kg-M**2) = 0.000067 STATIC MOMENT, ONE SIDE (IN-LB) = 0.038605 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 = 95.252 INNER LIMIT (NORMALIZED BY RADIUS) = 0.059 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8554.57 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.14, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.12, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412