S4233-136-84 (s4233-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 200,000 Max Cl/Cd: 77.75 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4233-il-200000.txt Download as CSV file: xf-s4233-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4233-136-84
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2368 0.08180 0.07884 -0.0604 0.9849 0.0684
-9.500 -0.2250 0.07744 0.07447 -0.0633 0.9803 0.0707
-9.250 -0.3761 0.08142 0.07843 -0.0610 0.9915 0.0666
-9.000 -0.3495 0.07956 0.07655 -0.0611 0.9875 0.0682
-8.750 -0.3307 0.07507 0.07205 -0.0668 0.9822 0.0707
-8.500 -0.2656 0.04689 0.04389 -0.0926 0.9499 0.0806
-8.250 -0.2697 0.04329 0.04023 -0.0943 0.9370 0.0819
-8.000 -0.2807 0.03998 0.03681 -0.0943 0.9236 0.0832
-7.750 -0.2900 0.03662 0.03330 -0.0939 0.9118 0.0855
-7.500 -0.3586 0.03539 0.03022 -0.0974 0.9158 0.0459
-7.250 -0.3514 0.03045 0.02415 -0.0940 0.9051 0.0352
-7.000 -0.3309 0.02823 0.02169 -0.0930 0.8989 0.0344
-6.750 -0.3123 0.02605 0.01924 -0.0918 0.8899 0.0340
-6.500 -0.2905 0.02427 0.01717 -0.0906 0.8843 0.0339
-6.250 -0.2682 0.02308 0.01576 -0.0896 0.8757 0.0344
-6.000 -0.2452 0.02163 0.01410 -0.0886 0.8699 0.0355
-5.750 -0.2224 0.02030 0.01274 -0.0878 0.8625 0.0365
-5.500 -0.1990 0.01925 0.01165 -0.0868 0.8561 0.0373
-5.250 -0.1758 0.01840 0.01076 -0.0859 0.8497 0.0386
-5.000 -0.1526 0.01765 0.00995 -0.0850 0.8426 0.0403
-4.750 -0.1287 0.01697 0.00916 -0.0840 0.8377 0.0427
-4.500 -0.1065 0.01620 0.00840 -0.0833 0.8296 0.0468
-4.250 -0.0823 0.01555 0.00771 -0.0826 0.8241 0.0570
-4.000 -0.0636 0.01394 0.00686 -0.0817 0.8172 0.1984
-3.750 -0.0411 0.01320 0.00658 -0.0811 0.8109 0.3202
-3.500 -0.0174 0.01271 0.00641 -0.0804 0.8062 0.4204
-3.250 0.0061 0.01249 0.00646 -0.0796 0.7985 0.5028
-3.000 0.0311 0.01235 0.00642 -0.0787 0.7933 0.5658
-2.750 0.0561 0.01235 0.00650 -0.0779 0.7870 0.6111
-2.500 0.0819 0.01234 0.00648 -0.0772 0.7807 0.6425
-2.250 0.1085 0.01229 0.00637 -0.0765 0.7762 0.6683
-2.000 0.1340 0.01235 0.00642 -0.0759 0.7688 0.6927
-1.750 0.1602 0.01230 0.00636 -0.0751 0.7633 0.7142
-1.500 0.1862 0.01231 0.00633 -0.0745 0.7578 0.7353
-1.250 0.2118 0.01232 0.00633 -0.0738 0.7511 0.7557
-1.000 0.2381 0.01226 0.00623 -0.0731 0.7463 0.7743
-0.750 0.2629 0.01229 0.00628 -0.0723 0.7395 0.7921
-0.500 0.2884 0.01225 0.00622 -0.0715 0.7336 0.8097
-0.250 0.3142 0.01222 0.00615 -0.0707 0.7287 0.8276
0.000 0.3380 0.01224 0.00620 -0.0697 0.7214 0.8461
0.250 0.3632 0.01218 0.00611 -0.0688 0.7163 0.8653
0.500 0.3867 0.01219 0.00615 -0.0676 0.7098 0.8843
0.750 0.4117 0.01216 0.00611 -0.0667 0.7036 0.9041
1.000 0.4407 0.01211 0.00600 -0.0665 0.6987 0.9249
1.250 0.4738 0.01215 0.00607 -0.0675 0.6911 0.9448
1.500 0.5159 0.01210 0.00595 -0.0703 0.6856 0.9611
1.750 0.5602 0.01215 0.00598 -0.0739 0.6783 0.9761
2.000 0.6077 0.01211 0.00589 -0.0781 0.6717 0.9884
2.250 0.6508 0.01213 0.00588 -0.0817 0.6647 1.0000
2.500 0.6665 0.01220 0.00591 -0.0799 0.6577 1.0000
2.750 0.6881 0.01230 0.00594 -0.0790 0.6516 1.0000
3.000 0.7107 0.01242 0.00605 -0.0783 0.6437 1.0000
3.250 0.7374 0.01251 0.00604 -0.0782 0.6379 1.0000
3.500 0.7614 0.01266 0.00623 -0.0777 0.6293 1.0000
3.750 0.7893 0.01274 0.00623 -0.0777 0.6233 1.0000
4.000 0.8135 0.01290 0.00646 -0.0772 0.6143 1.0000
4.250 0.8416 0.01299 0.00647 -0.0772 0.6079 1.0000
4.500 0.8660 0.01316 0.00671 -0.0768 0.5986 1.0000
4.750 0.8933 0.01327 0.00679 -0.0767 0.5914 1.0000
5.000 0.9185 0.01342 0.00698 -0.0763 0.5822 1.0000
5.250 0.9446 0.01356 0.00715 -0.0761 0.5738 1.0000
5.500 0.9709 0.01368 0.00727 -0.0758 0.5649 1.0000
5.750 0.9957 0.01385 0.00750 -0.0754 0.5551 1.0000
6.000 1.0221 0.01399 0.00761 -0.0751 0.5460 1.0000
6.250 1.0467 0.01413 0.00782 -0.0746 0.5352 1.0000
6.500 1.0709 0.01431 0.00805 -0.0741 0.5240 1.0000
6.750 1.0953 0.01446 0.00823 -0.0735 0.5124 1.0000
7.000 1.1193 0.01462 0.00841 -0.0729 0.4999 1.0000
7.250 1.1425 0.01480 0.00860 -0.0721 0.4865 1.0000
7.500 1.1651 0.01501 0.00883 -0.0713 0.4727 1.0000
7.750 1.1864 0.01526 0.00912 -0.0702 0.4575 1.0000
8.000 1.2061 0.01553 0.00945 -0.0690 0.4404 1.0000
8.250 1.2251 0.01585 0.00981 -0.0676 0.4226 1.0000
8.500 1.2425 0.01622 0.01019 -0.0660 0.4031 1.0000
8.750 1.2575 0.01667 0.01060 -0.0641 0.3815 1.0000
9.000 1.2689 0.01722 0.01112 -0.0617 0.3556 1.0000
9.250 1.2773 0.01788 0.01171 -0.0589 0.3280 1.0000
9.500 1.2808 0.01864 0.01239 -0.0554 0.3010 1.0000
9.750 1.2829 0.01959 0.01324 -0.0519 0.2743 1.0000
10.000 1.2844 0.02073 0.01428 -0.0488 0.2480 1.0000
10.250 1.2843 0.02209 0.01552 -0.0458 0.2201 1.0000
10.500 1.2824 0.02370 0.01702 -0.0430 0.1904 1.0000
10.750 1.2793 0.02557 0.01874 -0.0404 0.1610 1.0000
11.000 1.2744 0.02773 0.02074 -0.0380 0.1318 1.0000
11.250 1.2686 0.03012 0.02298 -0.0358 0.1052 1.0000
11.500 1.2600 0.03290 0.02557 -0.0338 0.0792 1.0000
11.750 1.2495 0.03603 0.02856 -0.0319 0.0588 1.0000
12.000 1.2393 0.03933 0.03180 -0.0304 0.0462 1.0000
12.250 1.2319 0.04253 0.03502 -0.0292 0.0405 1.0000
12.500 1.2275 0.04554 0.03808 -0.0284 0.0364 1.0000
12.750 1.2194 0.04906 0.04164 -0.0277 0.0341 1.0000
13.000 1.2199 0.05180 0.04450 -0.0272 0.0321 1.0000
13.250 1.2199 0.05467 0.04745 -0.0268 0.0304 1.0000
13.500 1.2193 0.05765 0.05048 -0.0266 0.0290 1.0000
13.750 1.2158 0.06090 0.05372 -0.0261 0.0275 1.0000
14.000 1.2212 0.06335 0.05630 -0.0259 0.0264 1.0000
14.250 1.2264 0.06580 0.05886 -0.0258 0.0255 1.0000
14.500 1.2317 0.06826 0.06140 -0.0255 0.0245 1.0000
14.750 1.2384 0.07056 0.06378 -0.0252 0.0239 1.0000
15.000 1.2454 0.07284 0.06611 -0.0249 0.0232 1.0000
15.250 1.2547 0.07488 0.06817 -0.0244 0.0226 1.0000
15.500 1.2714 0.07619 0.06950 -0.0228 0.0219 1.0000
15.750 1.2788 0.07888 0.07238 -0.0225 0.0216 1.0000
16.000 1.2839 0.08184 0.07553 -0.0225 0.0215 1.0000
16.250 1.2827 0.08563 0.07955 -0.0231 0.0213 1.0000
16.500 1.2818 0.08950 0.08364 -0.0237 0.0212 1.0000
16.750 1.2774 0.09390 0.08827 -0.0247 0.0212 1.0000
17.000 1.2695 0.09888 0.09347 -0.0263 0.0211 1.0000
17.250 1.2602 0.10419 0.09902 -0.0282 0.0211 1.0000
17.500 1.2481 0.11001 0.10507 -0.0307 0.0210 1.0000
17.750 1.2346 0.11629 0.11157 -0.0338 0.0210 1.0000
18.000 1.2205 0.12292 0.11842 -0.0371 0.0211 1.0000
18.250 1.2045 0.13013 0.12583 -0.0412 0.0212 1.0000
18.500 1.1875 0.13782 0.13372 -0.0458 0.0212 1.0000
18.750 1.1699 0.14598 0.14207 -0.0509 0.0214 1.0000
19.000 1.1526 0.15441 0.15065 -0.0562 0.0216 1.0000
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Polar data table (+)
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