WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 1,000,000 Max Cl/Cd: 154.45 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150b-il-1000000.txt Download as CSV file: xf-fx72150b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.3208 0.08813 0.08463 -0.1614 0.6669 0.0114
-9.500 0.3294 0.08608 0.08254 -0.1622 0.6628 0.0117
-9.250 0.3383 0.08385 0.08031 -0.1631 0.6591 0.0123
-9.000 0.3471 0.08156 0.07803 -0.1641 0.6558 0.0126
-8.750 0.3523 0.07898 0.07546 -0.1656 0.6522 0.0130
-8.500 0.3568 0.07668 0.07315 -0.1669 0.6483 0.0130
-8.250 0.3626 0.07437 0.07082 -0.1678 0.6443 0.0130
-8.000 0.3712 0.07215 0.06862 -0.1687 0.6413 0.0131
-7.750 0.3793 0.06958 0.06606 -0.1690 0.6379 0.0132
-7.500 0.3894 0.06780 0.06427 -0.1693 0.6340 0.0133
-7.250 0.3990 0.06616 0.06261 -0.1696 0.6301 0.0135
-7.000 0.4074 0.06441 0.06086 -0.1700 0.6267 0.0137
-6.750 0.4155 0.06260 0.05907 -0.1704 0.6235 0.0140
-6.500 0.4219 0.06074 0.05721 -0.1707 0.6202 0.0142
-6.250 0.4256 0.05890 0.05538 -0.1705 0.6168 0.0149
-6.000 0.4231 0.05582 0.05230 -0.1727 0.6135 0.0159
-5.750 0.4329 0.05286 0.04936 -0.1757 0.6106 0.0160
-5.500 0.4439 0.04944 0.04596 -0.1793 0.6081 0.0161
-5.250 0.4578 0.04775 0.04428 -0.1806 0.6051 0.0163
-5.000 0.4750 0.04567 0.04217 -0.1834 0.6022 0.0164
-4.750 0.4943 0.04348 0.03997 -0.1868 0.5992 0.0167
-4.500 0.5175 0.04080 0.03723 -0.1917 0.5959 0.0171
-4.250 0.5535 0.03631 0.03272 -0.2021 0.5939 0.0178
-4.000 0.6375 0.02297 0.01874 -0.2297 0.5920 0.0196
-3.750 0.6702 0.02156 0.01722 -0.2327 0.5896 0.0199
-3.500 0.7045 0.02007 0.01557 -0.2358 0.5871 0.0204
-3.250 0.7611 0.01434 0.00898 -0.2441 0.5848 0.0179
-3.000 0.7975 0.01262 0.00687 -0.2465 0.5822 0.0174
-2.750 0.8290 0.01192 0.00597 -0.2476 0.5794 0.0174
-2.500 0.8605 0.01139 0.00535 -0.2487 0.5777 0.0176
-2.250 0.8909 0.01109 0.00499 -0.2494 0.5757 0.0182
-2.000 0.9214 0.01080 0.00464 -0.2502 0.5737 0.0187
-1.750 0.9516 0.01057 0.00435 -0.2510 0.5714 0.0191
-1.500 0.9827 0.01024 0.00397 -0.2520 0.5691 0.0201
-1.250 1.0119 0.01016 0.00386 -0.2526 0.5667 0.0214
-1.000 1.0408 0.01016 0.00379 -0.2531 0.5639 0.0227
-0.750 1.0714 0.00999 0.00362 -0.2539 0.5626 0.0249
-0.500 1.1013 0.00990 0.00352 -0.2546 0.5610 0.0287
-0.250 1.1309 0.00983 0.00346 -0.2553 0.5593 0.0349
0.000 1.1602 0.00979 0.00345 -0.2558 0.5576 0.0512
0.250 1.1909 0.00961 0.00349 -0.2569 0.5558 0.1509
0.500 1.2232 0.00924 0.00364 -0.2587 0.5540 0.4184
0.750 1.2508 0.00933 0.00375 -0.2589 0.5522 0.4712
1.000 1.2782 0.00946 0.00387 -0.2591 0.5502 0.4923
1.250 1.3056 0.00962 0.00402 -0.2592 0.5480 0.5098
1.500 1.3332 0.00970 0.00411 -0.2595 0.5471 0.5224
1.750 1.3606 0.00979 0.00422 -0.2596 0.5461 0.5380
2.000 1.3880 0.00988 0.00434 -0.2598 0.5449 0.5509
2.250 1.4153 0.00998 0.00444 -0.2600 0.5436 0.5582
2.500 1.4424 0.01007 0.00455 -0.2602 0.5422 0.5645
2.750 1.4693 0.01018 0.00466 -0.2603 0.5408 0.5699
3.000 1.4961 0.01029 0.00477 -0.2604 0.5393 0.5756
3.250 1.5226 0.01040 0.00490 -0.2605 0.5379 0.5807
3.500 1.5490 0.01055 0.00504 -0.2606 0.5364 0.5860
3.750 1.5753 0.01071 0.00519 -0.2607 0.5350 0.5907
4.000 1.6021 0.01088 0.00538 -0.2609 0.5333 0.5956
4.250 1.6293 0.01108 0.00557 -0.2612 0.5318 0.6010
4.500 1.6555 0.01118 0.00571 -0.2612 0.5311 0.6066
4.750 1.6815 0.01128 0.00586 -0.2613 0.5303 0.6127
5.000 1.7073 0.01140 0.00603 -0.2613 0.5295 0.6197
5.250 1.7330 0.01152 0.00620 -0.2613 0.5285 0.6270
5.500 1.7585 0.01164 0.00638 -0.2613 0.5274 0.6352
5.750 1.7837 0.01177 0.00655 -0.2612 0.5262 0.6436
6.000 1.8085 0.01190 0.00674 -0.2611 0.5249 0.6533
6.250 1.8331 0.01204 0.00692 -0.2609 0.5235 0.6637
6.500 1.8572 0.01218 0.00712 -0.2607 0.5221 0.6760
7.000 1.9039 0.01257 0.00758 -0.2600 0.5166 0.7132
7.250 1.9223 0.01266 0.00780 -0.2586 0.5145 0.7495
7.500 1.9352 0.01253 0.00801 -0.2560 0.5124 1.0000
7.750 1.9537 0.01271 0.00824 -0.2548 0.5102 1.0000
8.000 1.9716 0.01292 0.00849 -0.2534 0.5077 1.0000
8.250 1.9879 0.01320 0.00878 -0.2518 0.5046 1.0000
8.500 2.0053 0.01358 0.00914 -0.2504 0.5006 1.0000
8.750 2.0199 0.01388 0.00953 -0.2486 0.4976 1.0000
9.000 2.0344 0.01424 0.00995 -0.2469 0.4931 1.0000
9.250 2.0457 0.01481 0.01051 -0.2447 0.4879 1.0000
9.500 2.0594 0.01534 0.01108 -0.2429 0.4830 1.0000
9.750 2.0744 0.01585 0.01165 -0.2415 0.4778 1.0000
10.000 2.0824 0.01672 0.01251 -0.2390 0.4713 1.0000
10.250 2.0953 0.01740 0.01326 -0.2374 0.4627 1.0000
10.500 2.1015 0.01849 0.01435 -0.2349 0.4523 1.0000
10.750 2.1054 0.01979 0.01564 -0.2322 0.4366 1.0000
11.000 2.0974 0.02193 0.01770 -0.2281 0.4166 1.0000
11.250 2.0827 0.02470 0.02039 -0.2235 0.3962 1.0000
11.500 2.0616 0.02816 0.02374 -0.2185 0.3660 1.0000
11.750 2.0361 0.03232 0.02780 -0.2135 0.3436 1.0000
12.000 2.0144 0.03651 0.03193 -0.2094 0.3223 1.0000
12.250 1.9885 0.04144 0.03677 -0.2053 0.2971 1.0000
12.500 1.9633 0.04660 0.04186 -0.2018 0.2766 1.0000
12.750 1.9396 0.05187 0.04707 -0.1987 0.2533 1.0000
13.000 1.9133 0.05770 0.05281 -0.1958 0.2307 1.0000
13.250 1.8910 0.06327 0.05831 -0.1934 0.2086 1.0000
13.500 1.8697 0.06894 0.06390 -0.1913 0.1873 1.0000
13.750 1.8514 0.07439 0.06926 -0.1896 0.1655 1.0000
14.000 1.8309 0.08027 0.07503 -0.1880 0.1410 1.0000
14.250 1.8140 0.08583 0.08049 -0.1868 0.1191 1.0000
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Polar data table (+)
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