EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 100,000 Max Cl/Cd: 36.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87151-il-100000-n5.txt Download as CSV file: xf-ste87151-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 871-514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4274 0.12089 0.11581 -0.0631 0.9798 0.0560
-10.750 -0.4363 0.11624 0.11120 -0.0662 0.9785 0.0562
-10.500 -0.4455 0.11118 0.10617 -0.0694 0.9773 0.0563
-10.250 -0.4440 0.09875 0.09366 -0.0699 0.9769 0.0275
-10.000 -0.4454 0.09525 0.09018 -0.0707 0.9759 0.0271
-9.750 -0.4512 0.09010 0.08503 -0.0739 0.9746 0.0266
-9.500 -0.4695 0.08615 0.08108 -0.0736 0.9725 0.0262
-9.250 -0.4903 0.08245 0.07737 -0.0728 0.9701 0.0259
-9.000 -0.5123 0.07907 0.07394 -0.0714 0.9671 0.0256
-8.750 -0.5354 0.07617 0.07097 -0.0691 0.9646 0.0253
-8.500 -0.5466 0.07209 0.06673 -0.0686 0.9620 0.0248
-8.250 -0.5612 0.06868 0.06317 -0.0657 0.9592 0.0244
-8.000 -0.5729 0.06506 0.05935 -0.0627 0.9558 0.0239
-7.750 -0.5785 0.06072 0.05470 -0.0606 0.9527 0.0233
-7.500 -0.5794 0.05599 0.04950 -0.0586 0.9505 0.0226
-7.250 -0.5722 0.05133 0.04419 -0.0572 0.9484 0.0220
-7.000 -0.5558 0.04905 0.04173 -0.0572 0.9468 0.0225
-6.750 -0.5482 0.04723 0.03974 -0.0548 0.9442 0.0232
-6.500 -0.5351 0.04526 0.03750 -0.0534 0.9422 0.0241
-6.250 -0.5177 0.04300 0.03485 -0.0524 0.9401 0.0250
-6.000 -0.4960 0.04064 0.03205 -0.0519 0.9382 0.0255
-5.750 -0.4714 0.03848 0.02948 -0.0517 0.9367 0.0257
-5.500 -0.4456 0.03666 0.02729 -0.0515 0.9356 0.0260
-5.250 -0.4181 0.03511 0.02543 -0.0515 0.9345 0.0265
-5.000 -0.3889 0.03382 0.02386 -0.0517 0.9334 0.0272
-4.750 -0.3660 0.03268 0.02261 -0.0509 0.9312 0.0284
-4.500 -0.3465 0.03185 0.02179 -0.0498 0.9276 0.0305
-4.250 -0.3204 0.03105 0.02093 -0.0497 0.9243 0.0327
-4.000 -0.2913 0.03023 0.02001 -0.0500 0.9218 0.0345
-3.750 -0.2617 0.02941 0.01915 -0.0507 0.9199 0.0366
-3.500 -0.2311 0.02887 0.01859 -0.0518 0.9184 0.0411
-3.250 -0.2138 0.02841 0.01808 -0.0502 0.9147 0.0463
-3.000 -0.1904 0.02796 0.01759 -0.0498 0.9114 0.0545
-2.750 -0.1632 0.02739 0.01719 -0.0500 0.9088 0.0826
-2.500 -0.1499 0.02509 0.01779 -0.0478 0.9072 0.6029
-2.250 -0.1318 0.02656 0.01934 -0.0436 0.9043 0.7703
-2.000 -0.1357 0.02755 0.02037 -0.0350 0.8985 0.8145
-1.750 -0.1424 0.02823 0.02109 -0.0246 0.8932 0.8529
-1.500 -0.1322 0.02853 0.02131 -0.0187 0.8900 0.8822
-1.250 -0.1086 0.02852 0.02113 -0.0185 0.8863 0.8875
-1.000 -0.0902 0.02842 0.02091 -0.0171 0.8811 0.8908
-0.750 -0.0618 0.02842 0.02074 -0.0176 0.8776 0.8935
-0.500 -0.0292 0.02845 0.02064 -0.0191 0.8749 0.8957
-0.250 -0.0075 0.02843 0.02051 -0.0186 0.8695 0.8984
0.000 0.0187 0.02840 0.02038 -0.0190 0.8642 0.9006
0.250 0.0520 0.02841 0.02029 -0.0205 0.8609 0.9021
0.500 0.0787 0.02840 0.02021 -0.0208 0.8562 0.9036
0.750 0.1011 0.02837 0.02013 -0.0204 0.8498 0.9053
1.000 0.1341 0.02837 0.02008 -0.0218 0.8464 0.9064
1.250 0.1594 0.02838 0.02006 -0.0220 0.8408 0.9078
1.500 0.1852 0.02837 0.02002 -0.0222 0.8346 0.9094
1.750 0.2202 0.02831 0.01994 -0.0239 0.8313 0.9101
2.000 0.2402 0.02831 0.01994 -0.0232 0.8228 0.9115
2.250 0.2734 0.02822 0.01985 -0.0246 0.8184 0.9126
2.500 0.2970 0.02820 0.01985 -0.0244 0.8104 0.9139
2.750 0.3297 0.02806 0.01974 -0.0257 0.8051 0.9145
3.000 0.3539 0.02802 0.01973 -0.0256 0.7963 0.9154
3.250 0.3878 0.02775 0.01950 -0.0269 0.7909 0.9162
3.500 0.4098 0.02764 0.01944 -0.0262 0.7807 0.9176
3.750 0.4453 0.02720 0.01907 -0.0276 0.7753 0.9184
4.000 0.4704 0.02695 0.01890 -0.0273 0.7643 0.9193
4.250 0.4964 0.02667 0.01870 -0.0271 0.7529 0.9201
4.500 0.5258 0.02621 0.01834 -0.0273 0.7419 0.9210
4.750 0.5572 0.02553 0.01775 -0.0276 0.7305 0.9217
5.000 0.5830 0.02502 0.01732 -0.0269 0.7141 0.9230
5.250 0.6092 0.02449 0.01687 -0.0263 0.6933 0.9244
5.500 0.6399 0.02373 0.01618 -0.0262 0.6678 0.9256
5.750 0.6832 0.02237 0.01477 -0.0274 0.6339 0.9262
6.000 0.7250 0.02140 0.01366 -0.0287 0.5791 0.9267
6.250 0.7616 0.02098 0.01282 -0.0294 0.4969 0.9271
6.500 0.7826 0.02148 0.01287 -0.0284 0.4170 0.9282
6.750 0.7973 0.02233 0.01334 -0.0267 0.3444 0.9295
7.000 0.8102 0.02327 0.01393 -0.0250 0.2803 0.9309
7.250 0.8237 0.02421 0.01458 -0.0234 0.2278 0.9324
7.500 0.8390 0.02510 0.01527 -0.0222 0.1885 0.9339
7.750 0.8548 0.02597 0.01601 -0.0210 0.1603 0.9358
8.000 0.8704 0.02686 0.01681 -0.0198 0.1404 0.9380
8.250 0.8865 0.02773 0.01762 -0.0188 0.1258 0.9403
8.500 0.9030 0.02858 0.01849 -0.0178 0.1151 0.9426
8.750 0.9194 0.02945 0.01941 -0.0167 0.1078 0.9448
9.000 0.9352 0.03034 0.02035 -0.0156 0.1017 0.9472
9.250 0.9511 0.03128 0.02133 -0.0145 0.0965 0.9498
9.500 0.9686 0.03215 0.02230 -0.0137 0.0913 0.9527
9.750 0.9849 0.03314 0.02332 -0.0129 0.0872 0.9561
10.000 1.0032 0.03416 0.02441 -0.0123 0.0839 0.9600
10.250 1.0235 0.03512 0.02553 -0.0119 0.0808 0.9649
10.500 1.0435 0.03611 0.02664 -0.0115 0.0778 0.9720
10.750 1.0607 0.03704 0.02762 -0.0109 0.0751 0.9976
11.000 1.0834 0.03837 0.02895 -0.0111 0.0723 0.9980
11.250 1.1048 0.03959 0.03045 -0.0110 0.0698 0.9980
11.500 1.1272 0.04098 0.03203 -0.0111 0.0676 0.9980
11.750 1.1484 0.04244 0.03367 -0.0111 0.0656 0.9980
12.000 1.1671 0.04392 0.03528 -0.0109 0.0637 0.9980
12.250 1.1855 0.04545 0.03686 -0.0108 0.0618 0.9980
12.500 1.2045 0.04741 0.03896 -0.0108 0.0600 0.9980
12.750 1.2145 0.04940 0.04133 -0.0097 0.0586 0.9980
13.000 1.2233 0.05166 0.04392 -0.0085 0.0574 0.9980
13.250 1.2280 0.05406 0.04662 -0.0071 0.0561 0.9980
13.500 1.2298 0.05652 0.04937 -0.0056 0.0549 0.9980
13.750 1.2292 0.05902 0.05212 -0.0041 0.0537 0.9980
14.000 1.2278 0.06151 0.05482 -0.0028 0.0526 0.9980
14.250 1.2266 0.06405 0.05753 -0.0017 0.0516 0.9980
14.500 1.2256 0.06672 0.06035 -0.0007 0.0508 0.9980
14.750 1.2233 0.06979 0.06356 0.0000 0.0500 0.9980
15.000 1.2144 0.07364 0.06760 0.0008 0.0494 0.9980
15.250 1.1927 0.07832 0.07261 0.0015 0.0491 0.9980
15.500 1.1685 0.08371 0.07830 0.0012 0.0489 0.9980
15.750 1.1413 0.09002 0.08491 -0.0002 0.0487 0.9980
16.000 1.1111 0.09752 0.09268 -0.0030 0.0487 0.9980
16.250 1.0772 0.10662 0.10202 -0.0077 0.0488 0.9980
16.500 1.0379 0.11813 0.11373 -0.0147 0.0490 0.9980
16.750 0.9823 0.13581 0.13156 -0.0265 0.0494 0.9980
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