WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 76-100 (fx76100-il) Reynolds number: 200,000 Max Cl/Cd: 47.1 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76100-il-200000.txt Download as CSV file: xf-fx76100-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7038 0.11053 0.10673 -0.0075 1.0000 0.0505
-12.250 -0.6951 0.10925 0.10544 -0.0062 1.0000 0.0515
-12.000 -0.9277 0.05715 0.05250 -0.0415 1.0000 0.0330
-11.750 -0.9467 0.05335 0.04853 -0.0407 1.0000 0.0332
-11.500 -0.9643 0.05019 0.04516 -0.0384 1.0000 0.0332
-11.250 -0.9759 0.04759 0.04238 -0.0352 1.0000 0.0335
-11.000 -0.9565 0.04736 0.04233 -0.0345 1.0000 0.0353
-10.750 -0.9698 0.04376 0.03838 -0.0312 1.0000 0.0353
-10.500 -0.9666 0.04181 0.03625 -0.0290 1.0000 0.0364
-10.250 -0.9663 0.03913 0.03325 -0.0262 1.0000 0.0373
-10.000 -0.9624 0.03648 0.03024 -0.0236 1.0000 0.0379
-9.750 -0.9547 0.03410 0.02750 -0.0211 1.0000 0.0386
-9.500 -0.9440 0.03225 0.02529 -0.0187 1.0000 0.0397
-9.250 -0.9328 0.02961 0.02233 -0.0166 1.0000 0.0412
-9.000 -0.9159 0.02802 0.02076 -0.0153 1.0000 0.0433
-8.750 -0.8985 0.02680 0.01941 -0.0138 1.0000 0.0454
-8.500 -0.8804 0.02552 0.01795 -0.0121 1.0000 0.0477
-8.250 -0.8615 0.02453 0.01672 -0.0105 1.0000 0.0496
-8.000 -0.8437 0.02256 0.01473 -0.0091 1.0000 0.0529
-7.750 -0.8244 0.02166 0.01381 -0.0076 1.0000 0.0563
-7.500 -0.8046 0.02075 0.01278 -0.0061 1.0000 0.0596
-7.250 -0.7865 0.01949 0.01151 -0.0044 1.0000 0.0636
-7.000 -0.7677 0.01871 0.01073 -0.0028 1.0000 0.0686
-6.750 -0.7482 0.01799 0.00989 -0.0012 1.0000 0.0737
-6.500 -0.7314 0.01702 0.00902 0.0008 1.0000 0.0811
-6.250 -0.7138 0.01621 0.00823 0.0027 1.0000 0.0900
-6.000 -0.6961 0.01548 0.00754 0.0046 1.0000 0.1025
-5.750 -0.6786 0.01476 0.00694 0.0064 1.0000 0.1217
-5.500 -0.6609 0.01412 0.00645 0.0083 1.0000 0.1513
-5.250 -0.6421 0.01363 0.00608 0.0099 1.0000 0.1844
-5.000 -0.6228 0.01324 0.00579 0.0115 1.0000 0.2133
-4.750 -0.6034 0.01290 0.00552 0.0130 1.0000 0.2382
-4.500 -0.5835 0.01260 0.00527 0.0145 1.0000 0.2628
-4.250 -0.5639 0.01230 0.00506 0.0161 1.0000 0.2868
-4.000 -0.5443 0.01200 0.00485 0.0176 1.0000 0.3127
-3.750 -0.5248 0.01172 0.00466 0.0191 1.0000 0.3409
-3.500 -0.5056 0.01143 0.00451 0.0207 1.0000 0.3723
-3.250 -0.4869 0.01114 0.00439 0.0224 1.0000 0.4091
-3.000 -0.4689 0.01083 0.00429 0.0243 1.0000 0.4531
-2.750 -0.4518 0.01052 0.00422 0.0263 1.0000 0.5048
-2.500 -0.4353 0.01023 0.00420 0.0285 1.0000 0.5624
-2.250 -0.4192 0.00997 0.00422 0.0309 1.0000 0.6239
-2.000 -0.4029 0.00976 0.00429 0.0333 1.0000 0.6852
-1.750 -0.3853 0.00963 0.00441 0.0356 1.0000 0.7473
-1.500 -0.3419 0.00966 0.00467 0.0328 0.9937 0.8142
-1.250 -0.2926 0.00979 0.00490 0.0289 0.9877 0.8665
-1.000 -0.2372 0.00995 0.00510 0.0238 0.9822 0.9028
-0.750 -0.1811 0.01012 0.00525 0.0185 0.9766 0.9273
-0.500 -0.1199 0.01027 0.00538 0.0121 0.9715 0.9423
-0.250 -0.0605 0.01036 0.00545 0.0062 0.9652 0.9515
0.000 0.0003 0.01041 0.00548 0.0000 0.9598 0.9598
0.250 0.0604 0.01036 0.00545 -0.0061 0.9517 0.9653
0.500 0.1205 0.01028 0.00538 -0.0122 0.9425 0.9716
0.750 0.1806 0.01011 0.00524 -0.0184 0.9264 0.9763
1.000 0.2373 0.00995 0.00509 -0.0238 0.9021 0.9821
1.250 0.2923 0.00978 0.00490 -0.0289 0.8666 0.9876
1.500 0.3418 0.00966 0.00467 -0.0328 0.8143 0.9937
1.750 0.3853 0.00963 0.00441 -0.0356 0.7468 1.0000
2.000 0.4028 0.00976 0.00429 -0.0333 0.6850 1.0000
2.250 0.4191 0.00998 0.00422 -0.0308 0.6226 1.0000
2.500 0.4352 0.01023 0.00419 -0.0285 0.5620 1.0000
2.750 0.4518 0.01052 0.00422 -0.0263 0.5050 1.0000
3.000 0.4689 0.01083 0.00429 -0.0242 0.4533 1.0000
3.250 0.4868 0.01114 0.00439 -0.0224 0.4091 1.0000
3.500 0.5056 0.01143 0.00451 -0.0207 0.3726 1.0000
3.750 0.5247 0.01172 0.00466 -0.0191 0.3405 1.0000
4.000 0.5443 0.01200 0.00485 -0.0176 0.3125 1.0000
4.250 0.5638 0.01229 0.00505 -0.0160 0.2867 1.0000
4.500 0.5833 0.01261 0.00527 -0.0145 0.2624 1.0000
4.750 0.6033 0.01290 0.00552 -0.0130 0.2379 1.0000
5.000 0.6228 0.01324 0.00579 -0.0115 0.2131 1.0000
5.250 0.6420 0.01363 0.00608 -0.0099 0.1845 1.0000
5.500 0.6608 0.01411 0.00645 -0.0082 0.1514 1.0000
5.750 0.6785 0.01477 0.00694 -0.0064 0.1218 1.0000
6.000 0.6959 0.01549 0.00755 -0.0045 0.1020 1.0000
6.250 0.7137 0.01622 0.00823 -0.0026 0.0897 1.0000
6.500 0.7314 0.01701 0.00901 -0.0008 0.0807 1.0000
6.750 0.7479 0.01802 0.00992 0.0012 0.0734 1.0000
7.000 0.7677 0.01870 0.01071 0.0028 0.0685 1.0000
7.250 0.7864 0.01951 0.01151 0.0044 0.0636 1.0000
7.500 0.8045 0.02080 0.01282 0.0061 0.0597 1.0000
7.750 0.8245 0.02168 0.01384 0.0076 0.0564 1.0000
8.000 0.8439 0.02264 0.01483 0.0091 0.0532 1.0000
8.250 0.8617 0.02466 0.01684 0.0104 0.0498 1.0000
8.500 0.8805 0.02554 0.01797 0.0121 0.0477 1.0000
8.750 0.8986 0.02679 0.01941 0.0138 0.0455 1.0000
9.000 0.9161 0.02787 0.02058 0.0153 0.0432 1.0000
9.250 0.9329 0.02956 0.02229 0.0166 0.0413 1.0000
9.500 0.9442 0.03220 0.02524 0.0187 0.0397 1.0000
9.750 0.9551 0.03409 0.02748 0.0210 0.0387 1.0000
10.000 0.9627 0.03644 0.03020 0.0235 0.0378 1.0000
10.250 0.9666 0.03904 0.03315 0.0262 0.0369 1.0000
10.500 0.9663 0.04190 0.03635 0.0290 0.0365 1.0000
10.750 0.9670 0.04416 0.03883 0.0314 0.0354 1.0000
11.000 0.9608 0.04696 0.04187 0.0342 0.0350 1.0000
11.250 0.9779 0.04745 0.04222 0.0350 0.0334 1.0000
11.500 0.9610 0.05048 0.04550 0.0386 0.0334 1.0000
11.750 0.9498 0.05333 0.04846 0.0405 0.0330 1.0000
12.000 0.9249 0.05738 0.05278 0.0413 0.0332 1.0000
12.250 0.7949 0.08058 0.07672 0.0237 0.0383 1.0000
12.500 0.7647 0.09160 0.08777 0.0166 0.0396 1.0000
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Polar data table (+)
Polar graphs
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