7x6 (7x6.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 2.1560 0.0000 0.0000 0.3250 0.0000 0.3789 0.0000 0.2463 0.0000 0.1900 0.0000 0.0000 0.0800 0.6225 2.5426 0.0100 -0.2171 0.3208 0.0087 0.3636 1.1403 0.2263 0.1736 0.1945 0.0104 0.0248 0.1600 0.5910 2.9086 0.0783 -0.4242 0.3162 0.0323 0.3488 4.4532 0.2061 0.1694 0.2067 0.0226 0.0311 0.2400 0.5609 3.2542 0.2592 -0.5646 0.3115 0.0667 0.3345 9.7547 0.1876 0.1623 0.2241 0.0360 0.0412 0.3200 0.5380 3.5794 0.6022 -0.5636 0.3068 0.1079 0.3208 16.6730 0.1726 0.1518 0.2447 0.0495 0.0544 0.4000 0.5269 3.8840 1.1451 -0.3596 0.3024 0.1523 0.3076 24.4954 0.1621 0.1394 0.2666 0.0625 0.0690 0.4800 0.5288 4.1682 1.9006 0.0893 0.2984 0.1962 0.2950 32.2189 0.1560 0.1264 0.2880 0.0740 0.0839 0.5600 0.5410 4.4318 2.8334 0.7826 0.2950 0.2359 0.2829 38.8431 0.1531 0.1142 0.3072 0.0833 0.0975 0.6400 0.5580 4.6750 3.8356 1.6474 0.2924 0.2677 0.2714 43.6468 0.1515 0.1035 0.3221 0.0894 0.1089 0.7200 0.5737 4.8978 4.7181 2.5179 0.2907 0.2879 0.2605 46.2039 0.1494 0.0949 0.3305 0.0915 0.1168 0.8000 0.5829 5.1000 5.2412 3.1527 0.2903 0.2928 0.2500 46.1978 0.1457 0.0888 0.3300 0.0890 0.1202 0.8802 0.5869 5.2822 5.4425 3.5294 0.2907 0.2870 0.2402 44.5398 0.1409 0.0840 0.3228 0.0838 0.1204 0.9643 0.5909 5.4511 5.6265 3.9045 0.2916 0.2806 0.2304 42.8805 0.1361 0.0792 0.3152 0.0789 0.1201 1.0486 0.5948 5.5978 5.7866 4.2581 0.2927 0.2741 0.2212 41.2915 0.1316 0.0747 0.3074 0.0746 0.1195 1.1329 0.5984 5.7217 5.9224 4.5847 0.2941 0.2674 0.2126 39.7599 0.1272 0.0703 0.2996 0.0707 0.1186 1.2172 0.6015 5.8228 6.0342 4.8801 0.2955 0.2604 0.2047 38.2727 0.1231 0.0663 0.2918 0.0672 0.1174 1.3016 0.6042 5.9012 6.1222 5.1408 0.2969 0.2533 0.1973 36.8197 0.1192 0.0625 0.2838 0.0639 0.1160 1.3859 0.6064 5.9569 6.1867 5.3636 0.2981 0.2460 0.1906 35.3934 0.1156 0.0590 0.2758 0.0609 0.1144 1.4702 0.6078 5.9898 6.2277 5.5459 0.2991 0.2384 0.1845 33.9875 0.1121 0.0558 0.2677 0.0581 0.1125 1.5545 0.6085 6.0000 6.2457 5.6857 0.2998 0.2307 0.1790 32.5976 0.1089 0.0529 0.2595 0.0554 0.1105 1.6388 0.6083 6.0000 6.2535 5.7935 0.3000 0.2227 0.1741 31.2711 0.1059 0.0503 0.2512 0.0529 0.1083 1.7231 0.6071 6.0000 6.2614 5.8787 0.2996 0.2146 0.1698 30.0425 0.1031 0.0480 0.2428 0.0506 0.1055 1.8074 0.6048 6.0000 6.2698 5.9414 0.2986 0.2064 0.1661 28.9031 0.1005 0.0460 0.2344 0.0485 0.1024 1.8917 0.6014 6.0000 6.2789 5.9815 0.2968 0.1980 0.1631 27.8454 0.0981 0.0442 0.2258 0.0464 0.0990 1.9760 0.5966 6.0000 6.2887 5.9991 0.2941 0.1894 0.1606 26.8626 0.0958 0.0427 0.2172 0.0443 0.0952 2.0603 0.5904 6.0000 6.2991 6.0001 0.2905 0.1807 0.1586 25.9470 0.0937 0.0412 0.2084 0.0420 0.0911 2.1447 0.5827 6.0000 6.3091 6.0002 0.2857 0.1720 0.1567 25.0889 0.0913 0.0396 0.1996 0.0394 0.0869 2.2290 0.5734 6.0000 6.3185 6.0003 0.2798 0.1634 0.1547 24.2829 0.0887 0.0378 0.1906 0.0365 0.0828 2.3133 0.5623 6.0000 6.3272 6.0003 0.2725 0.1548 0.1527 23.5242 0.0859 0.0359 0.1816 0.0331 0.0785 2.3976 0.5494 6.0000 6.3352 6.0003 0.2639 0.1462 0.1508 22.8085 0.0828 0.0338 0.1725 0.0292 0.0743 2.4819 0.5346 6.0000 6.3423 6.0003 0.2537 0.1377 0.1488 22.1321 0.0795 0.0316 0.1633 0.0247 0.0701 2.5662 0.5177 6.0000 6.3486 6.0002 0.2420 0.1292 0.1468 21.4913 0.0760 0.0293 0.1541 0.0195 0.0659 2.6505 0.4986 6.0000 6.3537 6.0002 0.2284 0.1207 0.1449 20.8828 0.0722 0.0268 0.1447 0.0136 0.0617 2.7348 0.4772 6.0000 6.3576 6.0002 0.2131 0.1123 0.1429 20.3036 0.0682 0.0242 0.1352 0.0069 0.0575 2.8191 0.4534 5.9924 6.3522 5.9925 0.1958 0.1039 0.1409 19.7287 0.0639 0.0216 0.1257 -0.0006 0.0535 2.9034 0.4271 5.9623 6.3226 5.9625 0.1765 0.0955 0.1390 19.1152 0.0594 0.0189 0.1160 -0.0091 0.0496 2.9878 0.3982 5.9096 6.2678 5.9097 0.1551 0.0871 0.1370 18.4630 0.0546 0.0162 0.1062 -0.0187 0.0459 3.0721 0.3666 5.8340 6.1871 5.8341 0.1313 0.0787 0.1350 17.7725 0.0495 0.0136 0.0964 -0.0292 0.0424 3.1564 0.3322 5.7358 6.0795 5.7358 0.1053 0.0704 0.1331 17.0427 0.0442 0.0110 0.0865 -0.0409 0.0389 3.2407 0.2947 5.6148 5.9430 5.6148 0.0767 0.0621 0.1311 16.2709 0.0386 0.0086 0.0764 -0.0537 0.0355 3.3215 0.2560 5.4774 5.7820 5.4774 0.0469 0.0542 0.1292 15.4856 0.0331 0.0064 0.0667 -0.0671 0.0322 3.3427 0.2454 5.4380 5.7344 5.4380 0.0387 0.0521 0.1287 15.2715 0.0316 0.0059 0.0642 -0.0708 0.0313 3.3604 0.2363 5.4040 5.6927 5.4040 0.0318 0.0504 0.1283 15.0894 0.0303 0.0054 0.0620 -0.0740 0.0306 3.3780 0.2272 5.3689 5.6491 5.3690 0.0246 0.0487 0.1279 14.9042 0.0291 0.0050 0.0599 -0.0772 0.0299 3.3957 0.2163 5.3329 5.6038 5.3332 0.0159 0.0466 0.1275 14.7161 0.0276 0.0046 0.0573 -0.0813 0.0289 3.4134 0.2026 5.2959 5.5565 5.2966 0.0044 0.0438 0.1271 14.5250 0.0257 0.0040 0.0538 -0.0868 0.0274 3.4311 0.1851 5.2579 5.5071 5.2708 -0.0106 0.0402 0.1267 14.3301 0.0234 0.0033 0.0494 -0.0943 0.0254 3.4487 0.1624 5.2188 5.4552 5.2635 -0.0308 0.0353 0.1262 14.1307 0.0205 0.0026 0.0434 -0.1046 0.0225 3.4664 0.1300 5.1788 5.4006 5.3011 -0.0604 0.0283 0.1258 13.9262 0.0164 0.0017 0.0348 -0.1199 0.0181 3.4841 0.0708 5.1378 5.3437 5.6379 -0.1161 0.0152 0.1254 13.7178 0.0089 0.0005 0.0187 -0.1494 0.0094 3.5000 0.0080 5.1000 5.1000 5.1000 -0.1754 0.0013 0.1250 13.0568 0.0010 0.0000 0.0013 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.026575 TOTAL WEIGHT (Kg) = 0.012052 TOTAL VOLUME (IN**3) = 0.432942 TOTAL PROJECTED AREA (IN**2) = 3.1799 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000121 MOMENT OF INERTIA (Kg-M**2) = 0.000014 STATIC MOMENT, ONE SIDE (IN-LB) = 0.013636 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 = 91.122 INNER LIMIT (NORMALIZED BY RADIUS) = 0.093 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28398.37 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.