S4233-136-84 (s4233-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 200,000 Max Cl/Cd: 76.99 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4233-il-200000-n5.txt Download as CSV file: xf-s4233-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3792 0.08948 0.08602 -0.0520 1.0000 0.0167
-10.500 -0.3875 0.08351 0.08011 -0.0550 1.0000 0.0164
-10.250 -0.4028 0.07591 0.07257 -0.0590 1.0000 0.0160
-10.000 -0.4480 0.05468 0.05108 -0.0808 0.9641 0.0152
-9.750 -0.4666 0.04686 0.04288 -0.0903 0.9369 0.0150
-9.500 -0.4854 0.04259 0.03823 -0.0907 0.9156 0.0148
-9.250 -0.4932 0.03918 0.03445 -0.0898 0.9009 0.0148
-9.000 -0.4947 0.03605 0.03090 -0.0884 0.8887 0.0147
-8.750 -0.4890 0.03344 0.02791 -0.0871 0.8789 0.0148
-8.500 -0.4788 0.03109 0.02517 -0.0858 0.8702 0.0148
-8.250 -0.4645 0.02909 0.02285 -0.0848 0.8617 0.0150
-8.000 -0.4480 0.02730 0.02072 -0.0837 0.8545 0.0151
-7.750 -0.4289 0.02572 0.01886 -0.0829 0.8469 0.0154
-7.500 -0.4085 0.02431 0.01719 -0.0821 0.8400 0.0156
-7.250 -0.3868 0.02314 0.01580 -0.0814 0.8333 0.0162
-7.000 -0.3640 0.02215 0.01458 -0.0808 0.8263 0.0169
-6.750 -0.3408 0.02122 0.01343 -0.0801 0.8205 0.0174
-6.500 -0.3183 0.02005 0.01220 -0.0796 0.8133 0.0178
-6.250 -0.2955 0.01913 0.01120 -0.0789 0.8074 0.0182
-6.000 -0.2720 0.01835 0.01035 -0.0784 0.8007 0.0186
-5.750 -0.2483 0.01763 0.00955 -0.0779 0.7944 0.0191
-5.500 -0.2242 0.01700 0.00881 -0.0774 0.7887 0.0197
-5.250 -0.1995 0.01642 0.00814 -0.0771 0.7819 0.0205
-5.000 -0.1745 0.01591 0.00750 -0.0766 0.7763 0.0215
-4.750 -0.1492 0.01540 0.00691 -0.0764 0.7699 0.0230
-4.500 -0.1234 0.01500 0.00644 -0.0761 0.7638 0.0257
-4.250 -0.0975 0.01458 0.00594 -0.0758 0.7585 0.0296
-4.000 -0.0715 0.01413 0.00549 -0.0756 0.7518 0.0394
-3.750 -0.0465 0.01350 0.00504 -0.0754 0.7463 0.0861
-3.500 -0.0217 0.01289 0.00472 -0.0753 0.7404 0.1592
-3.250 0.0026 0.01223 0.00448 -0.0752 0.7342 0.2610
-3.000 0.0277 0.01176 0.00428 -0.0749 0.7292 0.3493
-2.750 0.0525 0.01136 0.00422 -0.0746 0.7227 0.4411
-2.500 0.0781 0.01114 0.00417 -0.0742 0.7169 0.5066
-2.250 0.1049 0.01104 0.00409 -0.0739 0.7117 0.5448
-2.000 0.1318 0.01098 0.00406 -0.0736 0.7052 0.5757
-1.750 0.1589 0.01093 0.00399 -0.0733 0.6999 0.6033
-1.500 0.1862 0.01091 0.00395 -0.0731 0.6940 0.6277
-1.250 0.2132 0.01088 0.00392 -0.0729 0.6879 0.6490
-0.750 0.2676 0.01086 0.00387 -0.0724 0.6763 0.6864
-0.500 0.2948 0.01086 0.00384 -0.0722 0.6706 0.7032
-0.250 0.3219 0.01086 0.00382 -0.0720 0.6650 0.7196
0.000 0.3488 0.01086 0.00384 -0.0717 0.6587 0.7360
0.250 0.3758 0.01087 0.00382 -0.0714 0.6533 0.7525
0.500 0.4024 0.01088 0.00386 -0.0711 0.6469 0.7688
0.750 0.4289 0.01089 0.00387 -0.0708 0.6409 0.7850
1.000 0.4554 0.01091 0.00389 -0.0704 0.6353 0.8017
1.500 0.5075 0.01094 0.00396 -0.0694 0.6229 0.8369
1.750 0.5333 0.01097 0.00404 -0.0689 0.6163 0.8564
2.000 0.5599 0.01099 0.00408 -0.0685 0.6098 0.8778
2.250 0.5877 0.01102 0.00413 -0.0684 0.6036 0.9011
2.500 0.6184 0.01106 0.00419 -0.0690 0.5964 0.9266
2.750 0.6540 0.01111 0.00424 -0.0706 0.5899 0.9523
3.000 0.6919 0.01118 0.00432 -0.0729 0.5819 0.9809
3.250 0.7242 0.01128 0.00438 -0.0741 0.5751 1.0000
3.500 0.7495 0.01141 0.00452 -0.0738 0.5671 1.0000
3.750 0.7753 0.01155 0.00461 -0.0736 0.5602 1.0000
4.000 0.8010 0.01169 0.00477 -0.0734 0.5518 1.0000
4.250 0.8268 0.01185 0.00491 -0.0731 0.5443 1.0000
4.500 0.8524 0.01200 0.00509 -0.0729 0.5356 1.0000
4.750 0.8781 0.01217 0.00526 -0.0727 0.5275 1.0000
5.000 0.9035 0.01235 0.00544 -0.0724 0.5186 1.0000
5.250 0.9288 0.01253 0.00566 -0.0721 0.5094 1.0000
5.500 0.9538 0.01274 0.00585 -0.0717 0.5003 1.0000
5.750 0.9786 0.01294 0.00609 -0.0713 0.4897 1.0000
6.000 1.0030 0.01316 0.00635 -0.0709 0.4792 1.0000
6.250 1.0270 0.01340 0.00660 -0.0703 0.4682 1.0000
6.500 1.0504 0.01366 0.00686 -0.0697 0.4562 1.0000
6.750 1.0733 0.01394 0.00716 -0.0691 0.4427 1.0000
7.000 1.0953 0.01425 0.00749 -0.0682 0.4278 1.0000
7.250 1.1162 0.01460 0.00783 -0.0673 0.4115 1.0000
7.500 1.1365 0.01498 0.00820 -0.0662 0.3951 1.0000
7.750 1.1561 0.01538 0.00862 -0.0651 0.3780 1.0000
8.000 1.1736 0.01585 0.00907 -0.0636 0.3578 1.0000
8.250 1.1883 0.01643 0.00958 -0.0618 0.3354 1.0000
8.500 1.2001 0.01709 0.01016 -0.0595 0.3086 1.0000
8.750 1.2087 0.01781 0.01079 -0.0568 0.2825 1.0000
9.000 1.2131 0.01871 0.01158 -0.0536 0.2544 1.0000
9.250 1.2155 0.01982 0.01253 -0.0505 0.2240 1.0000
9.500 1.2169 0.02111 0.01366 -0.0476 0.1933 1.0000
10.000 1.2193 0.02410 0.01637 -0.0425 0.1376 1.0000
10.250 1.2206 0.02577 0.01791 -0.0404 0.1132 1.0000
10.500 1.2233 0.02744 0.01950 -0.0385 0.0948 1.0000
10.750 1.2264 0.02915 0.02116 -0.0369 0.0785 1.0000
11.000 1.2292 0.03097 0.02295 -0.0354 0.0643 1.0000
11.250 1.2305 0.03299 0.02491 -0.0340 0.0509 1.0000
11.500 1.2330 0.03498 0.02689 -0.0328 0.0408 1.0000
11.750 1.2349 0.03710 0.02902 -0.0317 0.0329 1.0000
12.000 1.2359 0.03937 0.03130 -0.0307 0.0268 1.0000
12.250 1.2382 0.04160 0.03360 -0.0299 0.0228 1.0000
12.500 1.2393 0.04402 0.03608 -0.0292 0.0200 1.0000
12.750 1.2410 0.04646 0.03862 -0.0286 0.0184 1.0000
13.000 1.2411 0.04916 0.04140 -0.0282 0.0173 1.0000
13.250 1.2420 0.05186 0.04422 -0.0279 0.0162 1.0000
13.500 1.2435 0.05460 0.04708 -0.0278 0.0156 1.0000
13.750 1.2441 0.05752 0.05011 -0.0279 0.0150 1.0000
14.000 1.2437 0.06062 0.05333 -0.0280 0.0144 1.0000
14.250 1.2415 0.06406 0.05685 -0.0284 0.0138 1.0000
14.500 1.2385 0.06770 0.06059 -0.0289 0.0134 1.0000
14.750 1.2384 0.07106 0.06409 -0.0295 0.0130 1.0000
15.000 1.2371 0.07463 0.06779 -0.0301 0.0126 1.0000
15.250 1.2357 0.07833 0.07162 -0.0310 0.0123 1.0000
15.500 1.2334 0.08222 0.07564 -0.0319 0.0120 1.0000
15.750 1.2310 0.08620 0.07973 -0.0330 0.0117 1.0000
16.000 1.2289 0.09019 0.08383 -0.0342 0.0115 1.0000
16.250 1.2268 0.09424 0.08800 -0.0354 0.0114 1.0000
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Polar data table (+)
Polar graphs
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