S1012 (s1012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 200,000 Max Cl/Cd: 39.99 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1012-il-200000-n5.txt Download as CSV file: xf-s1012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1012
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9459 0.09927 0.09494 -0.0227 1.0000 0.0243
-16.250 -0.9889 0.08587 0.08124 -0.0315 1.0000 0.0241
-16.000 -1.0124 0.07735 0.07253 -0.0370 1.0000 0.0242
-15.750 -1.0290 0.07069 0.06572 -0.0411 1.0000 0.0244
-15.500 -1.0438 0.06484 0.05969 -0.0443 1.0000 0.0245
-15.250 -1.0548 0.06007 0.05479 -0.0466 1.0000 0.0247
-15.000 -1.0632 0.05604 0.05062 -0.0481 1.0000 0.0250
-14.750 -1.0701 0.05248 0.04692 -0.0490 1.0000 0.0253
-14.500 -1.0752 0.04936 0.04366 -0.0493 1.0000 0.0256
-14.250 -1.0791 0.04652 0.04068 -0.0492 1.0000 0.0260
-14.000 -1.0805 0.04411 0.03813 -0.0488 1.0000 0.0266
-13.750 -1.0808 0.04185 0.03572 -0.0480 1.0000 0.0272
-13.500 -1.0794 0.03979 0.03348 -0.0471 1.0000 0.0280
-13.250 -1.0764 0.03789 0.03136 -0.0460 1.0000 0.0289
-13.000 -1.0722 0.03612 0.02945 -0.0447 1.0000 0.0296
-12.750 -1.0670 0.03460 0.02788 -0.0434 1.0000 0.0303
-12.500 -1.0595 0.03328 0.02648 -0.0420 1.0000 0.0311
-12.250 -1.0507 0.03206 0.02515 -0.0406 1.0000 0.0320
-12.000 -1.0409 0.03085 0.02383 -0.0392 1.0000 0.0331
-11.750 -1.0297 0.02971 0.02255 -0.0378 1.0000 0.0343
-11.500 -1.0171 0.02865 0.02133 -0.0364 1.0000 0.0357
-11.250 -1.0065 0.02761 0.02028 -0.0348 1.0000 0.0369
-11.000 -0.9935 0.02681 0.01942 -0.0333 1.0000 0.0385
-10.750 -0.9794 0.02602 0.01855 -0.0319 1.0000 0.0402
-10.500 -0.9644 0.02523 0.01764 -0.0304 1.0000 0.0420
-10.250 -0.9506 0.02441 0.01676 -0.0287 1.0000 0.0435
-10.000 -0.9386 0.02376 0.01611 -0.0267 1.0000 0.0454
-9.750 -0.9236 0.02323 0.01553 -0.0252 0.9967 0.0476
-9.250 -0.8682 0.02172 0.01385 -0.0270 0.9732 0.0535
-9.000 -0.8405 0.02111 0.01320 -0.0278 0.9654 0.0569
-8.750 -0.8123 0.02054 0.01251 -0.0284 0.9587 0.0604
-8.500 -0.7871 0.01988 0.01183 -0.0287 0.9523 0.0640
-8.250 -0.7620 0.01939 0.01129 -0.0287 0.9464 0.0678
-8.000 -0.7360 0.01893 0.01072 -0.0288 0.9417 0.0718
-7.750 -0.7143 0.01839 0.01019 -0.0281 0.9362 0.0759
-7.500 -0.6910 0.01798 0.00974 -0.0277 0.9314 0.0805
-7.250 -0.6666 0.01760 0.00927 -0.0273 0.9277 0.0853
-7.000 -0.6444 0.01715 0.00885 -0.0266 0.9237 0.0906
-6.750 -0.6214 0.01683 0.00846 -0.0260 0.9193 0.0964
-6.500 -0.5993 0.01644 0.00808 -0.0252 0.9154 0.1024
-6.250 -0.5760 0.01613 0.00774 -0.0245 0.9123 0.1098
-6.000 -0.5535 0.01578 0.00741 -0.0238 0.9095 0.1173
-5.750 -0.5302 0.01551 0.00711 -0.0232 0.9063 0.1259
-5.500 -0.5077 0.01518 0.00683 -0.0225 0.9032 0.1360
-5.250 -0.4846 0.01489 0.00657 -0.0218 0.9005 0.1475
-5.000 -0.4616 0.01460 0.00631 -0.0211 0.8979 0.1607
-4.750 -0.4387 0.01431 0.00607 -0.0203 0.8955 0.1769
-4.500 -0.4160 0.01402 0.00586 -0.0196 0.8927 0.1968
-4.250 -0.3934 0.01373 0.00567 -0.0189 0.8900 0.2209
-4.000 -0.3715 0.01340 0.00548 -0.0181 0.8875 0.2523
-3.750 -0.3503 0.01303 0.00529 -0.0171 0.8849 0.2929
-3.500 -0.3302 0.01260 0.00510 -0.0159 0.8823 0.3463
-3.250 -0.3117 0.01210 0.00490 -0.0144 0.8801 0.4163
-3.000 -0.2950 0.01156 0.00479 -0.0125 0.8775 0.5050
-2.750 -0.2783 0.01114 0.00496 -0.0101 0.8743 0.6156
-2.500 -0.2539 0.01129 0.00544 -0.0087 0.8719 0.6945
-2.250 -0.2287 0.01145 0.00560 -0.0079 0.8696 0.7280
-2.000 -0.2033 0.01156 0.00569 -0.0072 0.8673 0.7482
-1.750 -0.1773 0.01169 0.00578 -0.0065 0.8654 0.7635
-1.500 -0.1508 0.01182 0.00589 -0.0060 0.8635 0.7753
-1.250 -0.1265 0.01196 0.00602 -0.0053 0.8600 0.7863
-1.000 -0.1008 0.01211 0.00619 -0.0046 0.8568 0.7958
-0.750 -0.0749 0.01224 0.00632 -0.0039 0.8538 0.8048
-0.500 -0.0499 0.01236 0.00643 -0.0029 0.8508 0.8166
-0.250 -0.0234 0.01260 0.00671 -0.0017 0.8476 0.8291
0.000 0.0000 0.01277 0.00692 0.0000 0.8394 0.8394
0.250 0.0234 0.01260 0.00670 0.0017 0.8290 0.8476
0.500 0.0499 0.01237 0.00643 0.0029 0.8166 0.8508
0.750 0.0749 0.01224 0.00632 0.0039 0.8048 0.8538
1.000 0.1009 0.01212 0.00619 0.0046 0.7959 0.8568
1.250 0.1265 0.01196 0.00602 0.0053 0.7864 0.8600
1.500 0.1508 0.01182 0.00590 0.0060 0.7754 0.8635
1.750 0.1773 0.01169 0.00578 0.0065 0.7637 0.8654
2.000 0.2033 0.01156 0.00569 0.0072 0.7481 0.8674
2.250 0.2287 0.01145 0.00560 0.0079 0.7280 0.8696
2.500 0.2539 0.01130 0.00545 0.0087 0.6949 0.8719
2.750 0.2783 0.01114 0.00496 0.0101 0.6153 0.8743
3.000 0.2950 0.01155 0.00479 0.0125 0.5053 0.8774
3.250 0.3116 0.01210 0.00490 0.0144 0.4163 0.8801
3.500 0.3302 0.01260 0.00510 0.0159 0.3460 0.8823
3.750 0.3504 0.01303 0.00529 0.0171 0.2934 0.8849
4.000 0.3715 0.01340 0.00548 0.0181 0.2526 0.8874
4.250 0.3935 0.01373 0.00566 0.0189 0.2211 0.8900
4.500 0.4160 0.01402 0.00586 0.0196 0.1968 0.8927
4.750 0.4387 0.01431 0.00607 0.0203 0.1771 0.8955
5.000 0.4616 0.01460 0.00631 0.0211 0.1607 0.8979
5.250 0.4846 0.01489 0.00657 0.0218 0.1474 0.9005
5.500 0.5077 0.01518 0.00683 0.0225 0.1359 0.9033
5.750 0.5301 0.01551 0.00711 0.0232 0.1259 0.9063
6.000 0.5535 0.01578 0.00740 0.0238 0.1173 0.9095
6.250 0.5761 0.01612 0.00774 0.0245 0.1096 0.9123
6.500 0.5993 0.01644 0.00808 0.0252 0.1024 0.9154
6.750 0.6214 0.01683 0.00846 0.0260 0.0965 0.9193
7.000 0.6444 0.01715 0.00885 0.0266 0.0906 0.9237
7.250 0.6666 0.01760 0.00927 0.0273 0.0852 0.9277
7.500 0.6910 0.01799 0.00974 0.0277 0.0805 0.9315
7.750 0.7143 0.01839 0.01019 0.0281 0.0759 0.9362
8.000 0.7361 0.01892 0.01071 0.0288 0.0718 0.9418
8.250 0.7621 0.01939 0.01128 0.0287 0.0679 0.9464
8.500 0.7872 0.01988 0.01182 0.0286 0.0639 0.9524
8.750 0.8124 0.02054 0.01250 0.0284 0.0604 0.9587
9.000 0.8407 0.02110 0.01319 0.0277 0.0568 0.9654
9.250 0.8685 0.02172 0.01385 0.0269 0.0535 0.9732
9.750 0.9239 0.02322 0.01553 0.0251 0.0476 0.9968
10.000 0.9387 0.02377 0.01612 0.0267 0.0454 1.0000
10.250 0.9508 0.02442 0.01676 0.0287 0.0436 1.0000
10.500 0.9647 0.02523 0.01764 0.0303 0.0420 1.0000
10.750 0.9796 0.02602 0.01855 0.0318 0.0401 1.0000
11.000 0.9938 0.02680 0.01942 0.0333 0.0384 1.0000
11.250 1.0068 0.02763 0.02030 0.0348 0.0370 1.0000
11.500 1.0173 0.02866 0.02134 0.0364 0.0356 1.0000
11.750 1.0301 0.02971 0.02255 0.0377 0.0343 1.0000
12.000 1.0413 0.03086 0.02383 0.0392 0.0331 1.0000
12.250 1.0511 0.03205 0.02515 0.0406 0.0320 1.0000
12.500 1.0599 0.03328 0.02647 0.0420 0.0310 1.0000
12.750 1.0673 0.03459 0.02787 0.0433 0.0303 1.0000
13.000 1.0728 0.03610 0.02943 0.0446 0.0296 1.0000
13.250 1.0770 0.03788 0.03137 0.0459 0.0288 1.0000
13.500 1.0798 0.03982 0.03351 0.0470 0.0280 1.0000
13.750 1.0812 0.04187 0.03574 0.0480 0.0272 1.0000
14.000 1.0809 0.04415 0.03818 0.0487 0.0266 1.0000
14.250 1.0794 0.04659 0.04076 0.0491 0.0261 1.0000
14.500 1.0764 0.04929 0.04359 0.0492 0.0256 1.0000
14.750 1.0716 0.05238 0.04682 0.0489 0.0253 1.0000
15.000 1.0650 0.05590 0.05046 0.0480 0.0249 1.0000
15.250 1.0559 0.06002 0.05473 0.0465 0.0247 1.0000
15.500 1.0449 0.06480 0.05966 0.0442 0.0245 1.0000
15.750 1.0312 0.07045 0.06546 0.0411 0.0243 1.0000
16.000 1.0138 0.07726 0.07243 0.0369 0.0242 1.0000
16.250 0.9914 0.08556 0.08092 0.0315 0.0241 1.0000
16.500 0.9484 0.09894 0.09460 0.0227 0.0243 1.0000
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Polar data table (+)
Polar graphs
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