9.5x7N (95x7N.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 0.9000 6.0320 0.0000 0.0000 0.4500 0.0000 0.4911 0.0000 0.4419 0.0000 0.1700 0.0000 0.0000 0.1200 0.8601 6.1347 0.0153 -0.5903 0.4450 0.0066 0.4605 1.1623 0.3961 0.3747 0.1737 0.0124 -0.0799 0.2400 0.8164 6.2317 0.1194 -1.1468 0.4419 0.0245 0.4314 4.5283 0.3522 0.3609 0.1835 0.0323 -0.0772 0.3600 0.7763 6.3229 0.3932 -1.5226 0.4402 0.0504 0.4038 9.8605 0.3134 0.3383 0.1976 0.0548 -0.0700 0.4800 0.7473 6.4083 0.9059 -1.5635 0.4399 0.0814 0.3775 16.7195 0.2821 0.3086 0.2142 0.0783 -0.0592 0.6000 0.7351 6.4880 1.7045 -1.1512 0.4405 0.1147 0.3527 24.3295 0.2593 0.2760 0.2316 0.1012 -0.0464 0.7200 0.7403 6.5619 2.7908 -0.2300 0.4417 0.1474 0.3293 31.6703 0.2438 0.2438 0.2481 0.1220 -0.0331 0.8400 0.7584 6.6301 4.0909 1.1415 0.4434 0.1768 0.3074 37.7795 0.2331 0.2146 0.2621 0.1390 -0.0208 0.9600 0.7818 6.6925 5.4281 2.7372 0.4453 0.1998 0.2868 41.9840 0.2243 0.1901 0.2718 0.1507 -0.0105 1.0800 0.8020 6.7491 6.5240 4.1477 0.4470 0.2138 0.2677 43.8731 0.2147 0.1715 0.2755 0.1560 -0.0031 1.2000 0.8129 6.8000 7.0562 4.8510 0.4482 0.2158 0.2501 43.1023 0.2033 0.1592 0.2710 0.1538 0.0006 1.3195 0.8164 6.8449 7.1229 4.9726 0.4491 0.2093 0.2339 40.6679 0.1909 0.1482 0.2597 0.1479 0.0016 1.4301 0.8179 6.8814 7.1714 5.1950 0.4497 0.2030 0.2202 38.5937 0.1801 0.1335 0.2473 0.1435 0.0027 1.5402 0.8179 6.9129 7.2118 5.4755 0.4501 0.1964 0.2077 36.6949 0.1699 0.1176 0.2346 0.1398 0.0040 1.6503 0.8165 6.9396 7.2453 5.7597 0.4503 0.1894 0.1965 34.9440 0.1604 0.1033 0.2226 0.1363 0.0055 1.7603 0.8137 6.9613 7.2726 6.0175 0.4501 0.1820 0.1864 33.3261 0.1517 0.0926 0.2122 0.1329 0.0073 1.8704 0.8095 6.9783 7.2947 6.2320 0.4496 0.1742 0.1776 31.8280 0.1437 0.0855 0.2034 0.1294 0.0095 1.9805 0.8039 6.9904 7.3121 6.4147 0.4486 0.1659 0.1699 30.4385 0.1366 0.0808 0.1956 0.1260 0.0117 2.0906 0.7969 6.9976 7.3274 6.5975 0.4470 0.1575 0.1635 29.1539 0.1303 0.0766 0.1877 0.1227 0.0132 2.2007 0.7885 7.0000 7.3435 6.7632 0.4449 0.1491 0.1582 27.9721 0.1248 0.0729 0.1796 0.1192 0.0139 2.3108 0.7787 7.0000 7.3612 6.8966 0.4421 0.1406 0.1542 26.8852 0.1201 0.0694 0.1708 0.1156 0.0135 2.4209 0.7674 7.0000 7.3824 6.9806 0.4386 0.1317 0.1513 25.8892 0.1161 0.0663 0.1611 0.1126 0.0118 2.5309 0.7547 7.0000 7.4076 6.9997 0.4343 0.1223 0.1497 24.9768 0.1129 0.0633 0.1506 0.1105 0.0086 2.6410 0.7404 7.0000 7.4351 6.9990 0.4291 0.1125 0.1483 24.1351 0.1098 0.0602 0.1398 0.1090 0.0047 2.7511 0.7246 7.0000 7.4649 6.9977 0.4230 0.1026 0.1469 23.3573 0.1065 0.0571 0.1288 0.1078 0.0005 2.8612 0.7073 7.0000 7.4965 6.9954 0.4159 0.0925 0.1455 22.6360 0.1029 0.0538 0.1177 0.1069 -0.0040 2.9713 0.6884 7.0000 7.5226 6.9933 0.4078 0.0819 0.1442 21.9465 0.0992 0.0504 0.1065 0.1060 -0.0088 3.0814 0.6680 7.0000 7.5371 6.9929 0.3985 0.0708 0.1428 21.2707 0.0954 0.0470 0.0949 0.1049 -0.0140 3.1915 0.6459 7.0000 7.5502 6.9927 0.3881 0.0596 0.1414 20.6323 0.0913 0.0435 0.0832 0.1035 -0.0194 3.3016 0.6221 7.0000 7.5622 6.9925 0.3764 0.0483 0.1400 20.0291 0.0871 0.0400 0.0713 0.1016 -0.0251 3.4116 0.5967 7.0000 7.5732 6.9924 0.3634 0.0370 0.1387 19.4580 0.0827 0.0364 0.0592 0.0992 -0.0311 3.5217 0.5697 7.0000 7.5828 6.9922 0.3490 0.0256 0.1373 18.9158 0.0782 0.0329 0.0470 0.0962 -0.0372 3.6318 0.5408 7.0000 7.5912 6.9926 0.3332 0.0142 0.1359 18.4004 0.0735 0.0293 0.0346 0.0926 -0.0436 3.7419 0.5103 7.0000 7.5979 6.9932 0.3159 0.0027 0.1345 17.9088 0.0686 0.0259 0.0221 0.0883 -0.0501 3.8520 0.4780 7.0000 7.6020 6.9940 0.2969 -0.0088 0.1332 17.4374 0.0636 0.0225 0.0094 0.0833 -0.0569 3.9621 0.4438 7.0000 7.6030 6.9948 0.2763 -0.0205 0.1318 16.9833 0.0585 0.0192 -0.0035 0.0774 -0.0638 4.0722 0.4078 6.9781 7.5778 6.9737 0.2541 -0.0322 0.1304 16.4976 0.0532 0.0161 -0.0165 0.0707 -0.0708 4.1822 0.3700 6.8605 7.4504 6.8569 0.2300 -0.0441 0.1290 15.8294 0.0477 0.0131 -0.0297 0.0629 -0.0776 4.2923 0.3303 6.6411 7.2128 6.6384 0.2041 -0.0563 0.1276 14.9730 0.0422 0.0104 -0.0431 0.0540 -0.0843 4.4024 0.2887 6.3199 6.8614 6.3180 0.1763 -0.0685 0.1263 13.9311 0.0364 0.0079 -0.0566 0.0441 -0.0910 4.5080 0.2469 5.9161 6.4115 5.9150 0.1477 -0.0804 0.1249 12.7543 0.0309 0.0058 -0.0697 0.0336 -0.0977 4.5365 0.2353 5.7911 6.2699 5.7902 0.1397 -0.0836 0.1246 12.4057 0.0293 0.0052 -0.0733 0.0306 -0.0996 4.5605 0.2255 5.6806 6.1436 5.6799 0.1329 -0.0863 0.1243 12.1012 0.0280 0.0048 -0.0763 0.0281 -0.1012 4.5845 0.2155 5.5653 6.0106 5.5646 0.1259 -0.0890 0.1240 11.7864 0.0267 0.0044 -0.0793 0.0254 -0.1028 4.6085 0.2055 5.4451 5.8705 5.4446 0.1188 -0.0917 0.1237 11.4608 0.0254 0.0040 -0.0824 0.0227 -0.1044 4.6324 0.1954 5.3200 5.7231 5.3197 0.1117 -0.0944 0.1234 11.1239 0.0241 0.0036 -0.0854 0.0200 -0.1061 4.6564 0.1833 5.1902 5.5681 5.1902 0.1027 -0.0974 0.1231 10.7754 0.0226 0.0032 -0.0889 0.0163 -0.1080 4.6804 0.1655 5.0555 5.4053 5.0677 0.0879 -0.1015 0.1228 10.4149 0.0203 0.0026 -0.0936 0.0096 -0.1106 4.7044 0.1389 4.9159 5.2336 5.0057 0.0645 -0.1069 0.1225 10.0406 0.0170 0.0018 -0.1002 -0.0018 -0.1144 4.7284 0.0907 4.7716 5.0521 5.1889 0.0198 -0.1157 0.1222 9.6507 0.0111 0.0008 -0.1113 -0.0243 -0.1205 4.7500 0.0072 4.6375 4.6375 4.6375 -0.0602 -0.1297 0.1219 8.8323 0.0009 0.0000 -0.1297 0.0000 0.0000 RADIUS: 4.75 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.064299 TOTAL WEIGHT (Kg) = 0.029161 TOTAL VOLUME (IN**3) = 1.047515 TOTAL PROJECTED AREA (IN**2) = 5.5628 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000400 MOMENT OF INERTIA (Kg-M**2) = 0.000045 STATIC MOMENT, ONE SIDE (IN-LB) = 0.037435 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 = 74.116 INNER LIMIT (NORMALIZED BY RADIUS) = 0.095 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 21701.08 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.