EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 200,000 Max Cl/Cd: 52.23 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87151-il-200000-n5.txt Download as CSV file: xf-ste87151-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1542 0.09341 0.08940 -0.1116 0.9487 0.0179
-11.750 -0.1553 0.08927 0.08527 -0.1128 0.9483 0.0172
-11.250 -0.2731 0.08483 0.08069 -0.1168 0.9507 0.0147
-11.000 -0.2741 0.08023 0.07611 -0.1197 0.9496 0.0146
-10.750 -0.2796 0.07359 0.06946 -0.1252 0.9484 0.0143
-10.500 -0.2948 0.06786 0.06366 -0.1288 0.9463 0.0141
-10.250 -0.3151 0.06390 0.05964 -0.1290 0.9433 0.0140
-10.000 -0.3355 0.06059 0.05624 -0.1279 0.9402 0.0138
-9.750 -0.3542 0.05748 0.05301 -0.1262 0.9370 0.0137
-9.500 -0.3723 0.05480 0.05019 -0.1235 0.9346 0.0136
-9.250 -0.3947 0.05329 0.04857 -0.1180 0.9314 0.0134
-9.000 -0.4263 0.05314 0.04839 -0.1087 0.9258 0.0134
-8.750 -0.4414 0.05085 0.04593 -0.1039 0.9228 0.0133
-8.500 -0.4448 0.04737 0.04217 -0.1013 0.9207 0.0131
-8.250 -0.4442 0.04388 0.03832 -0.0989 0.9192 0.0129
-8.000 -0.4658 0.04292 0.03724 -0.0905 0.9144 0.0129
-7.750 -0.4724 0.04075 0.03480 -0.0854 0.9111 0.0128
-7.500 -0.4657 0.03805 0.03174 -0.0827 0.9088 0.0128
-7.250 -0.4514 0.03547 0.02877 -0.0811 0.9072 0.0129
-7.000 -0.4335 0.03325 0.02618 -0.0799 0.9060 0.0132
-6.750 -0.4120 0.03139 0.02397 -0.0792 0.9052 0.0136
-6.500 -0.3870 0.02984 0.02197 -0.0788 0.9044 0.0147
-6.250 -0.3606 0.02851 0.02046 -0.0790 0.9038 0.0153
-6.000 -0.3521 0.02785 0.01972 -0.0757 0.9008 0.0156
-5.750 -0.3420 0.02719 0.01897 -0.0725 0.8979 0.0159
-5.500 -0.3221 0.02640 0.01809 -0.0712 0.8960 0.0163
-5.250 -0.2988 0.02561 0.01722 -0.0706 0.8943 0.0169
-5.000 -0.2745 0.02489 0.01642 -0.0702 0.8929 0.0176
-4.750 -0.2496 0.02424 0.01570 -0.0699 0.8918 0.0184
-4.500 -0.2230 0.02358 0.01502 -0.0701 0.8906 0.0196
-4.250 -0.1942 0.02312 0.01456 -0.0708 0.8896 0.0219
-4.000 -0.1634 0.02257 0.01396 -0.0717 0.8886 0.0241
-3.750 -0.1511 0.02228 0.01366 -0.0692 0.8840 0.0259
-3.500 -0.1301 0.02199 0.01331 -0.0683 0.8807 0.0288
-3.250 -0.1030 0.02161 0.01293 -0.0685 0.8785 0.0356
-3.000 -0.0736 0.02117 0.01257 -0.0693 0.8769 0.0535
-2.750 -0.0420 0.01986 0.01216 -0.0717 0.8758 0.2506
-2.500 -0.0236 0.01875 0.01305 -0.0697 0.8747 0.6700
-2.250 0.0082 0.01929 0.01349 -0.0702 0.8735 0.7538
-2.000 0.0104 0.02030 0.01453 -0.0639 0.8676 0.7847
-1.750 0.0146 0.02110 0.01539 -0.0572 0.8632 0.8068
-1.500 0.0357 0.02136 0.01559 -0.0552 0.8611 0.8181
-1.250 0.0647 0.02137 0.01552 -0.0555 0.8596 0.8216
-1.000 0.0971 0.02134 0.01539 -0.0567 0.8585 0.8243
-0.750 0.1193 0.02144 0.01542 -0.0562 0.8542 0.8273
-0.500 0.1422 0.02149 0.01542 -0.0559 0.8497 0.8294
-0.250 0.1701 0.02146 0.01534 -0.0561 0.8472 0.8308
0.000 0.2021 0.02134 0.01517 -0.0570 0.8453 0.8320
0.250 0.2364 0.02116 0.01495 -0.0584 0.8437 0.8331
0.750 0.2819 0.02116 0.01491 -0.0572 0.8328 0.8363
1.000 0.3151 0.02100 0.01474 -0.0585 0.8307 0.8373
1.250 0.3504 0.02077 0.01449 -0.0601 0.8290 0.8381
1.750 0.4007 0.02061 0.01435 -0.0598 0.8170 0.8407
2.000 0.4372 0.02026 0.01401 -0.0616 0.8149 0.8413
2.250 0.4553 0.02033 0.01410 -0.0603 0.8047 0.8428
2.500 0.4918 0.01987 0.01366 -0.0619 0.8016 0.8435
2.750 0.5112 0.01981 0.01364 -0.0606 0.7907 0.8443
3.000 0.5351 0.01960 0.01348 -0.0600 0.7809 0.8449
3.250 0.5673 0.01902 0.01293 -0.0605 0.7741 0.8454
3.500 0.5892 0.01876 0.01273 -0.0594 0.7605 0.8464
3.750 0.6155 0.01833 0.01233 -0.0589 0.7444 0.8472
4.000 0.6465 0.01764 0.01163 -0.0590 0.7212 0.8478
4.250 0.7014 0.01587 0.00975 -0.0625 0.6827 0.8478
4.500 0.7621 0.01459 0.00801 -0.0673 0.6116 0.8475
4.750 0.7805 0.01505 0.00809 -0.0656 0.5366 0.8482
5.000 0.7886 0.01585 0.00853 -0.0624 0.4675 0.8491
5.250 0.7971 0.01669 0.00905 -0.0594 0.4055 0.8501
5.500 0.8072 0.01754 0.00960 -0.0568 0.3476 0.8511
5.750 0.8188 0.01838 0.01017 -0.0546 0.2927 0.8524
6.000 0.8323 0.01921 0.01075 -0.0528 0.2417 0.8534
6.250 0.8476 0.01999 0.01130 -0.0514 0.1986 0.8542
6.500 0.8646 0.02070 0.01185 -0.0503 0.1647 0.8549
6.750 0.8824 0.02138 0.01240 -0.0492 0.1395 0.8556
7.000 0.9010 0.02202 0.01297 -0.0483 0.1199 0.8563
7.250 0.9196 0.02266 0.01356 -0.0475 0.1057 0.8571
7.500 0.9383 0.02329 0.01416 -0.0466 0.0956 0.8578
7.750 0.9571 0.02393 0.01479 -0.0457 0.0882 0.8584
8.000 0.9748 0.02456 0.01546 -0.0446 0.0830 0.8591
8.250 0.9926 0.02517 0.01613 -0.0435 0.0784 0.8598
8.500 1.0088 0.02589 0.01687 -0.0423 0.0743 0.8607
8.750 1.0251 0.02661 0.01764 -0.0410 0.0710 0.8617
9.000 1.0425 0.02727 0.01840 -0.0399 0.0681 0.8627
9.250 1.0592 0.02800 0.01920 -0.0388 0.0655 0.8636
9.500 1.0748 0.02883 0.02007 -0.0376 0.0633 0.8644
9.750 1.0886 0.02982 0.02108 -0.0362 0.0613 0.8653
10.000 1.1046 0.03067 0.02203 -0.0350 0.0598 0.8661
10.250 1.1213 0.03148 0.02296 -0.0340 0.0581 0.8670
10.500 1.1376 0.03232 0.02391 -0.0329 0.0563 0.8680
10.750 1.1532 0.03322 0.02489 -0.0319 0.0546 0.8690
11.000 1.1683 0.03417 0.02592 -0.0308 0.0532 0.8700
11.250 1.1827 0.03521 0.02703 -0.0296 0.0520 0.8710
11.500 1.1968 0.03642 0.02827 -0.0285 0.0507 0.8719
11.750 1.2124 0.03755 0.02951 -0.0275 0.0497 0.8729
12.000 1.2272 0.03858 0.03071 -0.0264 0.0486 0.8739
12.250 1.2408 0.03966 0.03196 -0.0252 0.0473 0.8750
12.500 1.2539 0.04083 0.03328 -0.0240 0.0462 0.8761
12.750 1.2661 0.04204 0.03464 -0.0228 0.0451 0.8773
13.000 1.2768 0.04331 0.03602 -0.0215 0.0440 0.8786
13.250 1.2863 0.04461 0.03742 -0.0202 0.0429 0.8801
13.500 1.2949 0.04607 0.03895 -0.0189 0.0418 0.8817
13.750 1.3032 0.04774 0.04074 -0.0176 0.0407 0.8834
14.000 1.3091 0.04939 0.04264 -0.0162 0.0396 0.8853
14.250 1.3142 0.05116 0.04463 -0.0149 0.0384 0.8871
14.500 1.3181 0.05299 0.04666 -0.0137 0.0373 0.8889
14.750 1.3210 0.05486 0.04869 -0.0125 0.0362 0.8907
15.000 1.3235 0.05684 0.05080 -0.0114 0.0353 0.8927
15.250 1.3254 0.05894 0.05302 -0.0106 0.0345 0.8949
15.500 1.3261 0.06130 0.05548 -0.0098 0.0337 0.8974
15.750 1.3245 0.06410 0.05844 -0.0091 0.0330 0.8999
16.000 1.3201 0.06734 0.06197 -0.0087 0.0322 0.9026
16.250 1.3142 0.07078 0.06568 -0.0084 0.0314 0.9058
16.500 1.3074 0.07449 0.06962 -0.0084 0.0307 0.9097
16.750 1.3002 0.07837 0.07371 -0.0089 0.0299 0.9144
17.000 1.2925 0.08238 0.07791 -0.0096 0.0292 0.9206
17.250 1.2842 0.08647 0.08218 -0.0105 0.0286 0.9307
17.500 1.2730 0.09056 0.08645 -0.0115 0.0282 0.9980
17.750 1.2653 0.09546 0.09148 -0.0137 0.0277 0.9980
18.000 1.2569 0.10058 0.09671 -0.0163 0.0272 0.9980
18.250 1.2447 0.10650 0.10275 -0.0192 0.0268 0.9980
18.500 1.2224 0.11474 0.11125 -0.0238 0.0266 0.9980
18.750 1.1959 0.12430 0.12104 -0.0295 0.0264 0.9980
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