9.5x5MR (95x5MR.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 -1.5743 0.0000 0.0000 0.3250 0.0000 0.3538 0.0000 0.2300 0.0000 0.1000 0.0000 0.0000 0.0760 0.6367 -0.9949 0.0046 -0.1866 0.3208 0.0047 0.3508 0.5482 0.2234 0.1230 0.1021 0.0017 -0.0116 0.1520 0.6154 -0.4456 0.0363 -0.3599 0.3162 0.0176 0.3418 2.1763 0.2103 0.1194 0.1080 0.0079 -0.0065 0.2280 0.5911 0.0738 0.1226 -0.4968 0.3116 0.0369 0.3267 4.8930 0.1931 0.1150 0.1169 0.0164 0.0006 0.3040 0.5699 0.5631 0.2933 -0.5065 0.3076 0.0607 0.3055 8.7299 0.1741 0.1055 0.1275 0.0259 0.0101 0.3800 0.5575 1.0224 0.5724 -0.3072 0.3047 0.0871 0.2783 13.4804 0.1552 0.0925 0.1391 0.0348 0.0210 0.4560 0.5593 1.4516 0.9677 0.1428 0.3033 0.1144 0.2451 18.6630 0.1371 0.0790 0.1518 0.0415 0.0321 0.5320 0.5792 1.8509 1.4591 0.8242 0.3039 0.1409 0.2101 23.5813 0.1217 0.0667 0.1657 0.0447 0.0423 0.6080 0.6193 2.2201 1.9914 1.6030 0.3068 0.1648 0.1803 27.5322 0.1117 0.0571 0.1803 0.0433 0.0506 0.6840 0.6807 2.5593 2.4860 2.2955 0.3126 0.1844 0.1553 30.0467 0.1057 0.0514 0.1946 0.0360 0.0557 0.7600 0.7644 2.8684 2.8678 2.7869 0.3216 0.1978 0.1346 30.9869 0.1029 0.0517 0.2064 0.0204 0.0549 0.8386 0.8598 3.1567 3.1567 3.1164 0.3329 0.2063 0.1174 30.9247 0.1009 0.0561 0.2150 -0.0017 0.0492 0.9628 0.9825 3.5464 3.5464 3.5491 0.3488 0.2152 0.0976 30.3808 0.0959 0.0605 0.2241 -0.0313 0.0417 1.0896 1.0721 3.8617 3.8617 3.8775 0.3628 0.2181 0.0850 29.4268 0.0911 0.0631 0.2276 -0.0522 0.0371 1.2163 1.1257 4.0934 4.0934 4.1092 0.3746 0.2149 0.0782 28.1742 0.0880 0.0642 0.2252 -0.0635 0.0352 1.3431 1.1434 4.2416 4.2416 4.2571 0.3843 0.2095 0.0751 26.6850 0.0859 0.0639 0.2209 -0.0649 0.0388 1.4699 1.1343 4.3077 4.3077 4.3240 0.3917 0.2038 0.0739 25.0058 0.0838 0.0619 0.2165 -0.0590 0.0473 1.5967 1.1220 4.3463 4.3463 4.3632 0.3971 0.1980 0.0729 23.4244 0.0818 0.0599 0.2120 -0.0532 0.0553 1.7234 1.1076 4.3850 4.3850 4.4025 0.4003 0.1920 0.0721 22.0450 0.0798 0.0579 0.2073 -0.0478 0.0618 1.8502 1.0912 4.4236 4.4236 4.4419 0.4015 0.1860 0.0714 20.8326 0.0779 0.0558 0.2023 -0.0430 0.0668 1.9770 1.0730 4.4622 4.4622 4.4815 0.4007 0.1797 0.0709 19.7595 0.0760 0.0536 0.1971 -0.0388 0.0706 2.1038 1.0528 4.5008 4.5008 4.5212 0.3980 0.1733 0.0704 18.8036 0.0742 0.0514 0.1917 -0.0354 0.0733 2.2305 1.0308 4.5394 4.5394 4.5611 0.3933 0.1667 0.0701 17.9472 0.0723 0.0491 0.1859 -0.0329 0.0750 2.3573 1.0071 4.5780 4.5780 4.6011 0.3867 0.1598 0.0699 17.1758 0.0704 0.0468 0.1798 -0.0312 0.0757 2.4841 0.9816 4.6167 4.6167 4.6414 0.3782 0.1527 0.0698 16.4776 0.0685 0.0444 0.1734 -0.0305 0.0755 2.6109 0.9545 4.6553 4.6553 4.6819 0.3679 0.1453 0.0697 15.8429 0.0665 0.0420 0.1665 -0.0308 0.0745 2.7376 0.9257 4.6939 4.6939 4.7227 0.3558 0.1376 0.0696 15.2634 0.0645 0.0396 0.1592 -0.0320 0.0728 2.8644 0.8954 4.7325 4.7325 4.7639 0.3420 0.1296 0.0696 14.7325 0.0624 0.0371 0.1514 -0.0343 0.0702 2.9912 0.8635 4.7711 4.7711 4.8057 0.3264 0.1213 0.0697 14.2443 0.0602 0.0346 0.1432 -0.0375 0.0669 3.1180 0.8302 4.8097 4.8097 4.8467 0.3092 0.1125 0.0697 13.7939 0.0579 0.0321 0.1344 -0.0421 0.0626 3.2447 0.7954 4.8483 4.8483 4.8814 0.2903 0.1031 0.0697 13.3771 0.0555 0.0299 0.1251 -0.0489 0.0570 3.3715 0.7593 4.8870 4.8870 4.9090 0.2698 0.0932 0.0697 12.9905 0.0530 0.0280 0.1152 -0.0578 0.0500 3.4983 0.7218 4.9256 4.9256 4.9301 0.2477 0.0828 0.0697 12.6307 0.0503 0.0262 0.1046 -0.0680 0.0420 3.6251 0.6830 4.9642 4.9642 4.9460 0.2241 0.0717 0.0697 12.2952 0.0476 0.0244 0.0934 -0.0792 0.0332 3.7518 0.6430 5.0028 5.0028 4.9587 0.1990 0.0602 0.0696 11.9816 0.0447 0.0225 0.0815 -0.0908 0.0238 3.8786 0.6018 5.0414 5.0414 4.9710 0.1725 0.0481 0.0694 11.6879 0.0418 0.0204 0.0689 -0.1027 0.0138 4.0054 0.5595 5.0800 5.0800 4.9862 0.1445 0.0355 0.0691 11.4122 0.0387 0.0182 0.0556 -0.1147 0.0034 4.1322 0.5161 5.1182 5.1182 5.0078 0.1151 0.0224 0.0687 11.1520 0.0355 0.0158 0.0414 -0.1267 -0.0073 4.2589 0.4717 5.1532 5.1532 5.0372 0.0840 0.0092 0.0682 10.9001 0.0322 0.0134 0.0270 -0.1392 -0.0178 4.3857 0.4253 5.1843 5.1843 5.0655 0.0461 0.0028 0.0676 10.6548 0.0288 0.0108 0.0186 -0.1569 -0.0218 4.5071 0.3683 5.2106 5.2106 5.0846 -0.0084 0.0030 0.0669 10.4255 0.0247 0.0080 0.0159 -0.1856 -0.0191 4.5365 0.3511 5.2164 5.2164 5.0931 -0.0258 0.0037 0.0667 10.3709 0.0234 0.0073 0.0157 -0.1952 -0.0177 4.5605 0.3358 5.2210 5.2210 5.1011 -0.0415 0.0044 0.0666 10.3264 0.0224 0.0067 0.0157 -0.2039 -0.0163 4.5845 0.3192 5.2255 5.2255 5.1107 -0.0587 0.0052 0.0664 10.2822 0.0212 0.0060 0.0157 -0.2134 -0.0148 4.6085 0.3018 5.2298 5.2298 5.1221 -0.0775 0.0061 0.0662 10.2381 0.0200 0.0054 0.0158 -0.2242 -0.0131 4.6324 0.2846 5.2340 5.2340 5.1348 -0.0988 0.0070 0.0661 10.1942 0.0188 0.0048 0.0159 -0.2376 -0.0115 4.6564 0.2660 5.2381 5.2381 5.1517 -0.1243 0.0074 0.0659 10.1505 0.0175 0.0042 0.0155 -0.2545 -0.0102 4.6804 0.2446 5.2420 5.2420 5.1779 -0.1552 0.0073 0.0657 10.1070 0.0161 0.0035 0.0145 -0.2754 -0.0092 4.7044 0.2173 5.2458 5.2458 5.2255 -0.1944 0.0061 0.0655 10.0636 0.0142 0.0028 0.0123 -0.3019 -0.0090 4.7284 0.1663 5.2495 5.2495 5.3874 -0.2491 0.0025 0.0653 10.0204 0.0109 0.0016 0.0071 -0.3325 -0.0094 4.7500 0.0087 5.2527 5.2550 5.2550 -0.3765 -0.0148 0.0651 9.9860 0.0006 0.0000 -0.0148 0.0000 0.0000 RADIUS: 4.77 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.76 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.027013 TOTAL WEIGHT (Kg) = 0.012251 TOTAL VOLUME (IN**3) = 0.440070 TOTAL PROJECTED AREA (IN**2) = 7.1207 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000283 MOMENT OF INERTIA (Kg-M**2) = 0.000032 STATIC MOMENT, ONE SIDE (IN-LB) = 0.021859 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 = 98.345 INNER LIMIT (NORMALIZED BY RADIUS) = 0.068 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 10319.44 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.04, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.51, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412