S4053 (s4053-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 200,000 Max Cl/Cd: 80.62 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4053-il-200000.txt Download as CSV file: xf-s4053-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4053
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3836 0.08840 0.08495 -0.0343 1.0000 0.0419
-8.000 -0.3912 0.08547 0.08210 -0.0363 1.0000 0.0428
-7.750 -0.4057 0.08271 0.07945 -0.0386 1.0000 0.0433
-7.500 -0.4119 0.07883 0.07560 -0.0429 1.0000 0.0436
-7.250 -0.4170 0.07527 0.07201 -0.0450 1.0000 0.0438
-7.000 -0.4231 0.07225 0.06893 -0.0449 1.0000 0.0439
-6.750 -0.4335 0.06702 0.06384 -0.0425 1.0000 0.0449
-6.500 -0.4368 0.06535 0.06226 -0.0387 1.0000 0.0458
-6.250 -0.4425 0.06346 0.06038 -0.0362 1.0000 0.0463
-6.000 -0.4161 0.05997 0.05684 -0.0401 0.9957 0.0495
-5.750 -0.3753 0.05141 0.04757 -0.0537 0.9869 0.0571
-5.500 -0.3487 0.04841 0.04482 -0.0554 0.9840 0.0605
-5.250 -0.3129 0.04401 0.03963 -0.0616 0.9746 0.0702
-5.000 -0.2828 0.03976 0.03557 -0.0644 0.9715 0.0732
-4.750 -0.2519 0.03687 0.03212 -0.0671 0.9625 0.0846
-4.500 -0.2183 0.03360 0.02895 -0.0699 0.9589 0.0890
-4.250 -0.1882 0.03097 0.02601 -0.0716 0.9511 0.1011
-4.000 -0.1450 0.02233 0.01583 -0.0708 0.9470 0.0406
-3.750 -0.1047 0.01991 0.01298 -0.0729 0.9443 0.0397
-3.500 -0.0724 0.01834 0.01112 -0.0734 0.9369 0.0400
-3.250 -0.0340 0.01666 0.00923 -0.0750 0.9329 0.0392
-3.000 0.0046 0.01534 0.00781 -0.0767 0.9293 0.0399
-2.750 0.0343 0.01445 0.00687 -0.0768 0.9207 0.0415
-2.500 0.0706 0.01351 0.00586 -0.0783 0.9161 0.0454
-2.250 0.0988 0.01296 0.00530 -0.0782 0.9066 0.0554
-2.000 0.1261 0.01120 0.00456 -0.0784 0.8998 0.2965
-1.750 0.1441 0.00996 0.00452 -0.0765 0.8902 0.6175
-1.500 0.2278 0.00910 0.00446 -0.0859 0.8919 0.9850
-1.250 0.2794 0.00895 0.00409 -0.0909 0.8864 1.0000
-1.000 0.3034 0.00895 0.00393 -0.0901 0.8749 1.0000
-0.750 0.3270 0.00899 0.00383 -0.0892 0.8638 1.0000
-0.500 0.3515 0.00904 0.00374 -0.0884 0.8538 1.0000
-0.250 0.3769 0.00908 0.00364 -0.0877 0.8445 1.0000
0.000 0.4000 0.00917 0.00364 -0.0867 0.8337 1.0000
0.250 0.4241 0.00927 0.00364 -0.0858 0.8240 1.0000
0.500 0.4497 0.00934 0.00360 -0.0851 0.8153 1.0000
0.750 0.4729 0.00945 0.00365 -0.0841 0.8045 1.0000
1.000 0.4971 0.00956 0.00369 -0.0832 0.7945 1.0000
1.250 0.5223 0.00965 0.00369 -0.0824 0.7852 1.0000
1.500 0.5463 0.00975 0.00375 -0.0815 0.7746 1.0000
1.750 0.5704 0.00987 0.00384 -0.0806 0.7641 1.0000
2.000 0.5954 0.00997 0.00389 -0.0798 0.7542 1.0000
2.250 0.6206 0.01007 0.00393 -0.0791 0.7440 1.0000
2.500 0.6446 0.01018 0.00403 -0.0781 0.7322 1.0000
2.750 0.6689 0.01028 0.00413 -0.0772 0.7204 1.0000
3.000 0.6936 0.01038 0.00421 -0.0764 0.7085 1.0000
3.250 0.7184 0.01047 0.00428 -0.0755 0.6963 1.0000
3.500 0.7431 0.01056 0.00436 -0.0747 0.6835 1.0000
3.750 0.7674 0.01065 0.00446 -0.0737 0.6693 1.0000
4.000 0.7913 0.01073 0.00455 -0.0727 0.6533 1.0000
4.250 0.8150 0.01081 0.00464 -0.0717 0.6358 1.0000
4.500 0.8387 0.01089 0.00472 -0.0706 0.6174 1.0000
4.750 0.8621 0.01100 0.00485 -0.0695 0.5971 1.0000
5.000 0.8850 0.01113 0.00497 -0.0683 0.5733 1.0000
5.250 0.9072 0.01129 0.00511 -0.0670 0.5458 1.0000
5.500 0.9287 0.01152 0.00527 -0.0656 0.5131 1.0000
5.750 0.9488 0.01184 0.00551 -0.0641 0.4728 1.0000
6.000 0.9676 0.01230 0.00580 -0.0623 0.4259 1.0000
6.250 0.9848 0.01291 0.00620 -0.0604 0.3738 1.0000
6.500 1.0012 0.01363 0.00669 -0.0585 0.3205 1.0000
6.750 1.0165 0.01448 0.00731 -0.0565 0.2669 1.0000
7.000 1.0307 0.01545 0.00800 -0.0545 0.2139 1.0000
7.250 1.0447 0.01648 0.00878 -0.0525 0.1680 1.0000
7.500 1.0581 0.01759 0.00968 -0.0503 0.1352 1.0000
7.750 1.0726 0.01863 0.01062 -0.0483 0.1125 1.0000
8.000 1.0867 0.01968 0.01159 -0.0463 0.0972 1.0000
8.250 1.1013 0.02070 0.01264 -0.0443 0.0862 1.0000
8.500 1.1151 0.02179 0.01374 -0.0423 0.0773 1.0000
8.750 1.1276 0.02302 0.01491 -0.0402 0.0690 1.0000
9.000 1.1442 0.02373 0.01577 -0.0386 0.0619 1.0000
9.250 1.1548 0.02512 0.01713 -0.0363 0.0557 1.0000
9.500 1.1682 0.02597 0.01812 -0.0342 0.0497 1.0000
9.750 1.1786 0.02769 0.01987 -0.0321 0.0442 1.0000
10.000 1.1902 0.02866 0.02099 -0.0299 0.0392 1.0000
10.250 1.2023 0.03102 0.02333 -0.0283 0.0348 1.0000
10.500 1.2153 0.03243 0.02497 -0.0264 0.0321 1.0000
10.750 1.2257 0.03384 0.02652 -0.0244 0.0295 1.0000
11.000 1.2359 0.03581 0.02851 -0.0229 0.0271 1.0000
11.250 1.2460 0.03865 0.03162 -0.0212 0.0255 1.0000
11.500 1.2522 0.04084 0.03411 -0.0191 0.0244 1.0000
11.750 1.2559 0.04342 0.03698 -0.0170 0.0236 1.0000
12.000 1.2558 0.04619 0.04003 -0.0149 0.0229 1.0000
12.250 1.2523 0.04920 0.04334 -0.0129 0.0224 1.0000
12.500 1.2455 0.05248 0.04689 -0.0112 0.0221 1.0000
12.750 1.2348 0.05623 0.05092 -0.0099 0.0220 1.0000
13.000 1.2246 0.05982 0.05473 -0.0092 0.0216 1.0000
13.250 1.2084 0.06440 0.05957 -0.0090 0.0215 1.0000
13.500 1.2002 0.06788 0.06318 -0.0094 0.0210 1.0000
13.750 1.1806 0.07342 0.06896 -0.0107 0.0210 1.0000
14.000 1.1392 0.08293 0.07889 -0.0145 0.0221 1.0000
14.250 1.1098 0.09138 0.08758 -0.0190 0.0225 1.0000
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Polar data table (+)
Polar graphs
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