WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 500,000 Max Cl/Cd: 117.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150b-il-500000-n5.txt Download as CSV file: xf-fx72150b-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.2676 0.09953 0.09519 -0.1528 0.6704 0.0130
-10.500 0.2755 0.09719 0.09283 -0.1539 0.6663 0.0130
-10.250 0.2797 0.09480 0.09042 -0.1553 0.6626 0.0131
-10.000 0.2922 0.09243 0.08804 -0.1556 0.6591 0.0132
-9.750 0.3008 0.09006 0.08568 -0.1566 0.6553 0.0132
-9.500 0.3116 0.08825 0.08385 -0.1572 0.6515 0.0135
-9.250 0.3208 0.08622 0.08181 -0.1580 0.6476 0.0138
-9.000 0.3292 0.08414 0.07970 -0.1588 0.6443 0.0139
-8.750 0.3381 0.08203 0.07760 -0.1597 0.6411 0.0142
-8.500 0.3465 0.07987 0.07544 -0.1605 0.6377 0.0144
-8.250 0.3547 0.07776 0.07334 -0.1613 0.6341 0.0148
-8.000 0.3627 0.07573 0.07130 -0.1620 0.6307 0.0149
-7.750 0.3677 0.07329 0.06885 -0.1631 0.6277 0.0157
-7.500 0.3710 0.07079 0.06637 -0.1644 0.6248 0.0159
-7.250 0.3756 0.06840 0.06400 -0.1654 0.6217 0.0159
-7.000 0.3803 0.06602 0.06164 -0.1661 0.6185 0.0160
-6.750 0.3843 0.06380 0.05941 -0.1664 0.6154 0.0160
-6.500 0.3873 0.06184 0.05745 -0.1662 0.6126 0.0160
-6.250 0.3933 0.06020 0.05583 -0.1658 0.6100 0.0162
-6.000 0.4041 0.05874 0.05439 -0.1659 0.6072 0.0164
-5.750 0.4137 0.05697 0.05263 -0.1668 0.6043 0.0166
-5.500 0.4240 0.05499 0.05065 -0.1683 0.6014 0.0168
-4.250 0.6158 0.01813 0.01219 -0.2343 0.5895 0.0133
-4.000 0.6498 0.01699 0.01080 -0.2367 0.5869 0.0136
-3.750 0.6829 0.01600 0.00956 -0.2386 0.5844 0.0139
-3.500 0.7147 0.01525 0.00859 -0.2401 0.5820 0.0143
-3.000 0.7774 0.01405 0.00698 -0.2424 0.5778 0.0156
-2.750 0.8084 0.01354 0.00633 -0.2434 0.5757 0.0159
-2.500 0.8391 0.01312 0.00584 -0.2444 0.5736 0.0162
-2.250 0.8691 0.01287 0.00555 -0.2452 0.5714 0.0168
-2.000 0.8988 0.01268 0.00532 -0.2459 0.5692 0.0174
-1.750 0.9285 0.01253 0.00509 -0.2466 0.5671 0.0184
-1.500 0.9579 0.01242 0.00490 -0.2472 0.5650 0.0193
-1.250 0.9874 0.01231 0.00477 -0.2479 0.5632 0.0205
-1.000 1.0166 0.01226 0.00470 -0.2484 0.5616 0.0227
-0.750 1.0462 0.01217 0.00461 -0.2491 0.5600 0.0252
-0.500 1.0754 0.01212 0.00453 -0.2497 0.5582 0.0282
-0.250 1.1043 0.01211 0.00450 -0.2502 0.5563 0.0330
0.000 1.1328 0.01209 0.00451 -0.2507 0.5544 0.0463
0.250 1.1616 0.01207 0.00454 -0.2513 0.5525 0.0831
0.500 1.1913 0.01195 0.00461 -0.2522 0.5507 0.1850
0.750 1.2222 0.01173 0.00478 -0.2536 0.5491 0.3909
1.000 1.2497 0.01182 0.00496 -0.2538 0.5476 0.4695
1.250 1.2769 0.01191 0.00510 -0.2540 0.5462 0.4963
1.500 1.3037 0.01203 0.00525 -0.2540 0.5446 0.5231
1.750 1.3304 0.01215 0.00539 -0.2541 0.5431 0.5402
2.000 1.3569 0.01228 0.00553 -0.2541 0.5414 0.5505
2.250 1.3832 0.01241 0.00565 -0.2541 0.5399 0.5577
2.500 1.4095 0.01255 0.00580 -0.2541 0.5384 0.5632
2.750 1.4356 0.01270 0.00593 -0.2541 0.5371 0.5684
3.000 1.4615 0.01286 0.00607 -0.2541 0.5358 0.5729
3.250 1.4874 0.01302 0.00623 -0.2541 0.5345 0.5766
3.500 1.5133 0.01320 0.00641 -0.2541 0.5332 0.5809
3.750 1.5394 0.01339 0.00659 -0.2542 0.5319 0.5856
4.250 1.5899 0.01369 0.00698 -0.2540 0.5299 0.5958
4.500 1.6147 0.01385 0.00719 -0.2538 0.5286 0.6015
4.750 1.6390 0.01402 0.00740 -0.2535 0.5272 0.6071
5.000 1.6631 0.01419 0.00762 -0.2532 0.5257 0.6127
5.250 1.6867 0.01437 0.00786 -0.2529 0.5242 0.6192
5.500 1.7098 0.01456 0.00809 -0.2524 0.5228 0.6258
5.750 1.7324 0.01475 0.00834 -0.2519 0.5215 0.6335
6.000 1.7547 0.01496 0.00858 -0.2513 0.5203 0.6426
6.250 1.7771 0.01517 0.00886 -0.2507 0.5192 0.6531
6.500 1.8000 0.01539 0.00913 -0.2503 0.5180 0.6638
6.750 1.8234 0.01563 0.00942 -0.2499 0.5169 0.6754
7.000 1.8468 0.01587 0.00973 -0.2496 0.5157 0.6894
7.500 1.8847 0.01637 0.01048 -0.2474 0.5129 0.7331
7.750 1.8997 0.01650 0.01088 -0.2456 0.5106 0.8367
8.000 1.9105 0.01678 0.01127 -0.2430 0.5073 1.0000
8.250 1.9254 0.01718 0.01170 -0.2413 0.5040 1.0000
8.500 1.9423 0.01760 0.01210 -0.2400 0.5007 1.0000
8.750 1.9555 0.01812 0.01274 -0.2382 0.4978 1.0000
9.000 1.9678 0.01871 0.01341 -0.2363 0.4940 1.0000
9.250 1.9791 0.01936 0.01411 -0.2343 0.4895 1.0000
9.500 1.9914 0.02005 0.01479 -0.2325 0.4854 1.0000
9.750 2.0019 0.02086 0.01572 -0.2306 0.4808 1.0000
10.000 2.0093 0.02185 0.01676 -0.2283 0.4744 1.0000
10.250 2.0156 0.02298 0.01793 -0.2260 0.4676 1.0000
10.500 2.0189 0.02436 0.01937 -0.2234 0.4578 1.0000
10.750 2.0205 0.02593 0.02100 -0.2208 0.4455 1.0000
11.000 2.0142 0.02815 0.02320 -0.2174 0.4286 1.0000
11.250 1.9983 0.03125 0.02623 -0.2132 0.4098 1.0000
11.500 1.9827 0.03465 0.02959 -0.2094 0.3878 1.0000
11.750 1.9551 0.03944 0.03428 -0.2049 0.3605 1.0000
12.000 1.9299 0.04438 0.03915 -0.2012 0.3419 1.0000
12.500 1.8811 0.05501 0.04967 -0.1949 0.2977 1.0000
12.750 1.8550 0.06089 0.05548 -0.1921 0.2778 1.0000
13.000 1.8336 0.06648 0.06102 -0.1900 0.2557 1.0000
13.250 1.8091 0.07263 0.06708 -0.1879 0.2321 1.0000
13.500 1.7888 0.07843 0.07280 -0.1863 0.2091 1.0000
13.750 1.7712 0.08404 0.07831 -0.1850 0.1867 1.0000
14.000 1.7568 0.08930 0.08348 -0.1839 0.1642 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il)