USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 200,000 Max Cl/Cd: 75.93 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa28-il-200000.txt Download as CSV file: xf-usa28-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 28 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5094 0.08121 0.07771 -0.0562 1.0000 0.0587
-10.250 -0.5083 0.07954 0.07608 -0.0551 1.0000 0.0593
-10.000 -0.7449 0.05382 0.04972 -0.0629 1.0000 0.0475
-9.750 -0.7646 0.05042 0.04617 -0.0592 1.0000 0.0473
-9.500 -0.7707 0.04727 0.04263 -0.0580 0.9976 0.0475
-9.250 -0.7654 0.04074 0.03564 -0.0600 0.9919 0.0484
-9.000 -0.7406 0.03854 0.03344 -0.0617 0.9874 0.0504
-8.750 -0.7152 0.03630 0.03098 -0.0632 0.9832 0.0520
-8.500 -0.6950 0.03391 0.02822 -0.0636 0.9770 0.0533
-8.250 -0.6664 0.03192 0.02583 -0.0651 0.9732 0.0552
-8.000 -0.6454 0.03051 0.02405 -0.0645 0.9659 0.0567
-7.750 -0.6164 0.02840 0.02156 -0.0657 0.9621 0.0580
-7.500 -0.5944 0.02630 0.01937 -0.0654 0.9561 0.0599
-7.250 -0.5639 0.02510 0.01807 -0.0665 0.9515 0.0623
-7.000 -0.5286 0.02397 0.01679 -0.0682 0.9488 0.0649
-6.750 -0.5060 0.02304 0.01571 -0.0673 0.9412 0.0666
-6.500 -0.4711 0.02228 0.01474 -0.0688 0.9375 0.0688
-6.250 -0.4375 0.02061 0.01311 -0.0703 0.9351 0.0725
-6.000 -0.4163 0.01987 0.01235 -0.0691 0.9267 0.0753
-5.750 -0.3805 0.01901 0.01140 -0.0707 0.9233 0.0794
-5.500 -0.3498 0.01806 0.01044 -0.0713 0.9184 0.0851
-5.250 -0.3209 0.01732 0.00968 -0.0714 0.9116 0.0937
-5.000 -0.2828 0.01637 0.00892 -0.0735 0.9085 0.1155
-4.750 -0.2407 0.01561 0.00831 -0.0762 0.9065 0.1726
-4.500 -0.2154 0.01531 0.00800 -0.0756 0.8977 0.1991
-4.250 -0.1754 0.01491 0.00759 -0.0781 0.8946 0.2201
-4.000 -0.1309 0.01451 0.00716 -0.0814 0.8923 0.2385
-3.750 -0.0977 0.01427 0.00694 -0.0824 0.8856 0.2537
-3.500 -0.0579 0.01402 0.00667 -0.0848 0.8804 0.2719
-3.250 -0.0128 0.01379 0.00650 -0.0883 0.8770 0.2922
-3.000 0.0187 0.01375 0.00646 -0.0889 0.8692 0.3106
-2.750 0.0565 0.01373 0.00638 -0.0908 0.8627 0.3339
-2.500 0.0916 0.01372 0.00636 -0.0920 0.8557 0.3526
-2.250 0.1211 0.01374 0.00632 -0.0922 0.8474 0.3686
-2.000 0.1575 0.01371 0.00623 -0.0938 0.8416 0.3838
-1.750 0.1810 0.01374 0.00623 -0.0927 0.8320 0.3955
-1.500 0.2150 0.01365 0.00611 -0.0938 0.8250 0.4073
-1.250 0.2388 0.01363 0.00605 -0.0928 0.8156 0.4173
-1.000 0.2702 0.01359 0.00593 -0.0934 0.8087 0.4279
-0.750 0.2939 0.01351 0.00588 -0.0924 0.8000 0.4355
-0.500 0.3274 0.01348 0.00574 -0.0935 0.7943 0.4451
-0.250 0.3476 0.01340 0.00574 -0.0918 0.7854 0.4519
0.000 0.3801 0.01335 0.00559 -0.0926 0.7791 0.4605
0.250 0.4010 0.01326 0.00559 -0.0911 0.7703 0.4670
0.500 0.4322 0.01319 0.00545 -0.0916 0.7636 0.4753
0.750 0.4537 0.01311 0.00545 -0.0903 0.7549 0.4828
1.000 0.4836 0.01302 0.00535 -0.0905 0.7481 0.4933
1.250 0.5056 0.01294 0.00536 -0.0892 0.7393 0.5029
1.500 0.5356 0.01280 0.00524 -0.0895 0.7319 0.5138
1.750 0.5568 0.01275 0.00525 -0.0880 0.7220 0.5240
2.000 0.5847 0.01260 0.00517 -0.0878 0.7134 0.5359
2.250 0.6081 0.01247 0.00515 -0.0868 0.7032 0.5510
2.500 0.6310 0.01232 0.00516 -0.0856 0.6930 0.5747
2.750 0.8260 0.01174 0.00561 -0.1220 0.6739 1.0000
3.000 0.8485 0.01188 0.00567 -0.1207 0.6608 1.0000
3.250 0.8708 0.01204 0.00575 -0.1194 0.6470 1.0000
3.500 0.8925 0.01223 0.00585 -0.1179 0.6323 1.0000
3.750 0.9138 0.01243 0.00599 -0.1164 0.6176 1.0000
4.000 0.9349 0.01265 0.00614 -0.1149 0.6031 1.0000
4.250 0.9554 0.01287 0.00630 -0.1132 0.5891 1.0000
4.500 0.9736 0.01308 0.00650 -0.1111 0.5748 1.0000
4.750 0.9918 0.01327 0.00670 -0.1090 0.5609 1.0000
5.000 1.0097 0.01344 0.00687 -0.1068 0.5470 1.0000
5.250 1.0282 0.01363 0.00704 -0.1048 0.5344 1.0000
5.500 1.0478 0.01384 0.00724 -0.1030 0.5234 1.0000
5.750 1.0670 0.01406 0.00746 -0.1011 0.5128 1.0000
6.000 1.0850 0.01429 0.00770 -0.0991 0.5013 1.0000
6.250 1.1011 0.01453 0.00791 -0.0966 0.4874 1.0000
6.500 1.1145 0.01482 0.00812 -0.0935 0.4703 1.0000
6.750 1.1279 0.01518 0.00839 -0.0905 0.4531 1.0000
7.000 1.1413 0.01557 0.00872 -0.0876 0.4366 1.0000
7.250 1.1546 0.01596 0.00909 -0.0847 0.4215 1.0000
7.500 1.1663 0.01634 0.00946 -0.0815 0.4062 1.0000
7.750 1.1756 0.01669 0.00983 -0.0778 0.3899 1.0000
8.000 1.1828 0.01699 0.01017 -0.0736 0.3742 1.0000
8.250 1.1870 0.01726 0.01048 -0.0689 0.3568 1.0000
8.500 1.1900 0.01757 0.01080 -0.0640 0.3339 1.0000
8.750 1.1866 0.01809 0.01121 -0.0582 0.2908 1.0000
9.000 1.1721 0.01933 0.01203 -0.0510 0.2244 1.0000
9.250 1.1530 0.02127 0.01346 -0.0440 0.1527 1.0000
9.500 1.1319 0.02369 0.01533 -0.0373 0.0825 1.0000
9.750 1.1234 0.02564 0.01708 -0.0327 0.0594 1.0000
10.000 1.1235 0.02716 0.01863 -0.0294 0.0521 1.0000
10.250 1.1205 0.02898 0.02046 -0.0260 0.0476 1.0000
10.500 1.1233 0.03050 0.02208 -0.0235 0.0447 1.0000
10.750 1.1245 0.03221 0.02386 -0.0210 0.0422 1.0000
11.000 1.1208 0.03435 0.02604 -0.0185 0.0402 1.0000
11.250 1.1185 0.03651 0.02825 -0.0162 0.0389 1.0000
11.500 1.1214 0.03836 0.03019 -0.0143 0.0374 1.0000
11.750 1.1244 0.04023 0.03214 -0.0126 0.0365 1.0000
12.000 1.1279 0.04213 0.03411 -0.0109 0.0354 1.0000
12.250 1.1325 0.04397 0.03598 -0.0094 0.0346 1.0000
12.500 1.1374 0.04584 0.03785 -0.0079 0.0334 1.0000
12.750 1.1497 0.04739 0.03931 -0.0059 0.0320 1.0000
13.000 1.1588 0.04896 0.04101 -0.0047 0.0313 1.0000
13.250 1.1688 0.05051 0.04267 -0.0035 0.0304 1.0000
13.500 1.1828 0.05196 0.04423 -0.0022 0.0298 1.0000
13.750 1.1962 0.05352 0.04589 -0.0010 0.0291 1.0000
14.000 1.2100 0.05518 0.04766 0.0002 0.0286 1.0000
14.250 1.2233 0.05700 0.04960 0.0013 0.0282 1.0000
14.500 1.2345 0.05905 0.05177 0.0024 0.0277 1.0000
14.750 1.2430 0.06132 0.05419 0.0034 0.0276 1.0000
15.000 1.2490 0.06390 0.05692 0.0044 0.0272 1.0000
15.250 1.2574 0.06647 0.05959 0.0052 0.0266 1.0000
15.500 1.2597 0.07094 0.06425 0.0061 0.0259 1.0000
15.750 1.2581 0.07449 0.06799 0.0068 0.0260 1.0000
16.000 1.2466 0.07828 0.07200 0.0072 0.0260 1.0000
16.250 1.2340 0.08262 0.07656 0.0074 0.0260 1.0000
16.500 1.2239 0.08618 0.08031 0.0073 0.0261 1.0000
16.750 1.2081 0.09045 0.08479 0.0066 0.0262 1.0000
17.000 1.1914 0.09524 0.08978 0.0055 0.0263 1.0000
17.250 1.1648 0.10118 0.09604 0.0030 0.0268 1.0000
17.500 1.1278 0.10985 0.10505 -0.0014 0.0272 1.0000
17.750 1.0670 0.12450 0.12019 -0.0100 0.0285 1.0000
18.000 1.0291 0.13634 0.13227 -0.0172 0.0293 1.0000
18.250 0.9920 0.14929 0.14540 -0.0252 0.0305 1.0000
18.500 0.9697 0.15946 0.15564 -0.0310 0.0314 1.0000
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